Pulse combustion heat exchanger system and method

ABSTRACT

A pulse combustion heat exchanger having a longitudinal axis is configured to accept oxidant and fuel and output a cooled combustion stream. The pulse combustion heat exchanger includes an oxidant inlet section that accepts oxidant, a fuel inlet section that accepts fuel, a mixing section that mixes oxidant with fuel, a combustion section that receives the oxidant and fuel and produces a pulsating combustion stream, and a heat transfer section configured to receive the pulsating combustion stream, the heat transfer section includes one or more resonance conduits. Coolant is employed at a plurality of longitudinally spaced-apart transition sections to remove heat.

TECHNICAL FIELD

The present disclosure relates to improvements to pulse combustion heatexchangers.

BACKGROUND

Efficient, reliable, and robust pulse combustion heat exchanger systemsare needed to meet industrial process heat transfer demands in suchareas as energy, chemicals, fuels, and materials processing. Pulsecombustion heat exchangers typically operate on the Helmholtz principleand offer advantages in comparison to conventional combustion-based firetube heat exchangers, including:

-   -   Periodic boundary layer scrubbing, reduced heat transfer        resistance and enhanced and more uniform heat flux rate to        reduce heat exchanger size for a specified heat transfer duty        and improve thermal efficiency;    -   High combustion efficiency;    -   Low NOx emissions and in turn improved environmental        performance;    -   Fuels flexibility.

Pulse combustion heat exchangers typically operate in an elevatedtemperature environment (1,000 to 1,500° F.). So, this heat exchangermust be carefully designed and engineered to minimize thermal stress andcreep, maximize structural integrity and equipment lifespan, and shouldbe capable of providing continuous operation and up-time whileminimizing maintenance and shut-down periods.

SUMMARY

This Summary is provided merely to introduce certain concepts and not toidentify any key or essential features of the claimed subject matter.

-   Paragraph A: A pulse combustion heat exchanger (1000) that is    configured to accept oxidant (1A1) and fuel (1A2) and output a    cooled combustion stream (1A5), including:    -   (a) an oxidant inlet section (100) that is configured to accept        oxidant (1A1);    -   (b) a fuel inlet section (200) that is configured to accept fuel        (1A2);    -   (c) a mixing section (300) including one or more aerovalves (A,        A′, A″, A′″, A^(N), A^(N+1)) that are configured to accept and        mix oxidant (1A1) from the oxidant inlet section (100) with fuel        (1A2) from the fuel inlet section (200) to create an oxidant and        fuel mixture (1A3);    -   (d) a combustion section (400) configured to receive and combust        the oxidant and fuel mixture (1A3) from the mixing section (300)        to produce a pulsating combustion stream (1A4);    -   (e) a heat transfer section (500) configured to receive the        combustion stream (1A4) from the combustion section (400), the        heat transfer section (500) including one or more resonance        conduits (502, 502A, 502B, 502C, 502D, 502E) that are configured        to transfer heat from the combustion stream (1A4) to an energy        sink (V108), wherein combustion of the oxidant and fuel mixture        (1A3) may continue to take place within the heat transfer        section (500);    -   (f) a first transition section (450) positioned between the        combustion section (400) and the heat transfer section (500),        the first transition section (450) comprising a first coolant        path configured to receive a first coolant (451);    -   (g) a second transition section (650) connected to the heat        transfer section (500) and configured to receive the combustion        stream (1A4) from the heat transfer section (500) and output a        cooled combustion stream (1A5), the second transition section        (650) comprising a second coolant path configured to receive a        second coolant (651); and    -   (h) a decoupler section (600) connected to the second transition        section (650) and configured to accept the cooled combustion        stream (1A5) from the second transition section (650) and output        the cooled combustion stream (1A5) via a combustion stream        outlet (606).-   Paragraph B: The pulse combustion heat exchanger (1000) according to    Paragraph A, wherein the first transition section (450) comprises:    -   a first pair of parallel tubesheets (403, 457) defining a first        interior space (450-1) therebetween;    -   a first coolant inlet (452) in fluid communication with the        first interior space (450-1) that is configured to receive the        first coolant (451); and    -   a first coolant outlet (454) in fluid communication with the        first interior space (450-1); wherein:    -   the first coolant inlet (452), the first interior space (450-1)        and the first coolant outlet (454) together define the first        coolant path through the first transition section (450).-   Paragraph C: The pulse combustion heat exchanger (1000) according to    Paragraph B, wherein the second transition section (650) comprises:    -   a second pair of parallel tubesheets (603, 657) defining a        second interior space (650-1) therebetween;    -   a second coolant inlet (652) in fluid communication with the        second interior space (650-1) that is configured to receive the        second coolant (652); and    -   a second coolant outlet (654) in fluid communication with the        second interior space (650-1); wherein:    -   the second coolant inlet (652), the second interior space        (650-1) and the second coolant outlet (654) together define the        second coolant path through the second transition section (450).-   Paragraph D: The pulse combustion heat exchanger (1000) according to    Paragraph A, further comprising:    -   a third transition section (350) positioned between the mixing        section (300) and the combustion section (400) that is provided        with a third coolant (351).-   Paragraph E: The pulse combustion heat exchanger (1000) according to    Paragraph D, wherein the third transition section (350) comprises:    -   a third pair of parallel tubesheets (357, 205) defining a third        interior space (350-1) therebetween;    -   a third coolant inlet (352) in fluid communication with the        third interior space (350-1) that is configured to receive the        third coolant (351); and    -   a third coolant outlet (354), in fluid communication with the        third interior space (350-1); wherein:    -   the third coolant inlet (352), the third interior space (350-1)        and the third coolant outlet (354) together define a third        coolant path through the third transition section (350).-   Paragraph F: The pulse combustion heat exchanger (1000) according to    Paragraph A, further comprising:    -   at least one ignitor (410, 410A, 410B) is in fluid communication        with the combustion section (400); and    -   an ignitor input (412) configured to introduce an ignitor        mixture (1A6) to the ignitor (410), the ignitor input (412)        being in fluid communication with an ignitor oxidant supply and        an ignitor fuel supply.-   Paragraph G: The pulse combustion heat exchanger (1000) according to    Paragraph F, further comprising:    -   a plurality of ignitors (410A, 410B) in fluid communication with        the combustion section (400).-   Paragraph H: The pulse combustion heat exchanger (1000) according to    Paragraph A, further comprising:    -   a vessel (V100) having an interior (V102) defined by at least        one side wall (V104); and    -   a heat transfer medium (V106) occupying the vessel's interior        (V102) and configured to accept heat from the heat transfer        section (500) and serve as an energy sink (V108).-   Paragraph I: The pulse combustion heat exchanger (1000) according to    Paragraph A, wherein:    -   the first transition section (450) is provided with a first        coolant inlet (452) and a first coolant outlet (454);    -   the second transition section (650) is provided with a second        coolant inlet (652) and a second coolant outlet (654);    -   the heat exchanger further comprises a coolant recycling drum        (800) having a drum outlet (812) in fluid communication with the        first and second coolant inlets (452, 652) and further having        drum inlet (822) in fluid communication with the first and        second coolant outlets (454, 654); and    -   a recycling pump (810) is interposed between the drum outlet        (812) and the first and second coolant inlets (452, 652), the        recycling pump (810) configured to supply coolant (815) under        pressure to the first and second coolant inlets (452, 652).-   Paragraph J: The pulse combustion heat exchanger (1000) according to    Paragraph I, further comprising:    -   a first restriction orifice (RO1) positioned between the        recycling pump (810) and the first coolant inlet (452); and    -   a second restriction orifice (RO2) positioned in between the        recycling pump (810) and the second coolant inlet (652).-   Paragraph K: The pulse combustion heat exchanger (1000) according to    Paragraph I, further comprising:    -   a third transition section (350) between the mixing section        (300) and the combustion section (400), the third transition        section (350) having a third coolant inlet (352) and a third        coolant outlet (354); wherein:    -   the drum outlet (812) is in fluid communication with the third        coolant inlet (352) and the drum inlet (822) is in fluid        communication with the third coolant outlet (354); and the        recycling pump (810) is interposed between the drum outlet (812)        and the third coolant inlet (352), the recycling pump (810)        configured to supply coolant (815) under pressure to the third        coolant inlet (352).-   Paragraph L: The pulse combustion heat exchanger (1000) according to    Paragraph K, further comprising:    -   a first restriction orifice (RO1) positioned between the        recycling pump (810) and the first coolant inlet (452);    -   a second restriction orifice (RO2) positioned in between the        recycling pump (810) and the second coolant inlet (652); and    -   a third restriction orifice (RO3) positioned between the coolant        recycling drum (800) and the third coolant inlet (352).-   Paragraph M: The pulse combustion heat exchanger (1000) according to    Paragraph A, further comprising:    -   a third transition section (350) between the mixing section        (300) and the combustion section (400), the third transition        section (350) having a third coolant inlet (352) and a third        coolant outlet (354);    -   a coolant recycling drum (800) having a drum outlet (812) in        fluid communication with the third coolant inlet (352) and        further having drum inlet (822) in fluid communication with the        third coolant outlet (354); and    -   a recycling pump (810) interposed between the drum outlet (812)        and the third coolant inlet (352), the recycling pump (810)        configured to supply coolant (815) under pressure to the third        coolant inlets (352).-   Paragraph N: The pulse combustion heat exchanger (1000) according to    Paragraph M, further comprising:    -   a third restriction orifice (RO3) positioned between the coolant        recycling drum (800) and the third coolant inlet (352).-   Paragraph O: The pulse combustion heat exchanger (1000) according to    Paragraph A, further comprising:    -   a plurality of fuel injectors (370A, 370B) location in the fuel        inlet section (200), each fuel injector including a fuel        injector conduit (372A, 372B) connected to a fuel injector        distributor (374A, 374B), wherein:    -   the fuel injector conduit (372A, 372B) is configured to accept        said fuel (1A2), and    -   fuel injector distributor (374A, 374B) is configured to transfer        the fuel (1A2) from the fuel injector conduit (372A, 372B) into        the mixing section (300).-   Paragraph P: A metal aerovalve (A), having an aerovalve longitudinal    axis (X1), an outer surface (S) with an outer diameter (D0), an    interior (A-IN), a rear end (1E1) having a rearwardly facing rear    surface (1E1S), a forward end (2E1) having a forwardly facing    forward surface (2E1S), and a total aerovalve length (L) defined    between the rear and forward ends (1E1, 2E1) along the aerovalve    longitudinal axis (X1), the aerovalve (A) further comprising:    -   an oxidant inlet (1A0) located at the rear end (1E1), the        oxidant inlet (1A0) configured to introduce oxidant (1A1) into        the interior (A-IN) of the aerovalve (A);    -   an oxidant and fuel mixture outlet (2A0) located at the forward        end (2E1), the oxidant and fuel mixture outlet (2A0) configured        to expel an oxidant and fuel mixture (1A3) present in the        interior (A-IN) of the aerovalve (A);    -   a first plurality of fuel inlet ports (1A, 1B, 1C, 1 ^(N), 1        ^(N+1)) opening to the outer surface (S), a second plurality of        fuel outlet ports (2A, 2B, 2C, 2 ^(N), 2 ^(N+1)) opening to the        interior (A-IN), and a third plurality of fuel transfer channels        (3A, 3B, 3C, 3 ^(N), 3 ^(N+1)) configured to transfer fuel (1A2)        from the first plurality of fuel inlet ports (1A, 1B, 1C, 1        ^(N), 1 ^(N+1)) to the second plurality of fuel outlet ports        (2A, 2B, 2C, 2 ^(N), 2 ^(N+1));    -   a first inner conical surface (S1) tapering radially inwardly at        a first angle (A1) to a first inner diameter (D1), the first        inner conical surface (S1) extending in the forward direction        from proximate the rear end (1E1) for a first length (L1) along        the aerovalve longitudinal axis (X1);    -   a second inner conical surface (S2) expanding radially outwardly        at a second angle (A2) to a second inner diameter (D2), the        second inner conical surface (S2) extending in the forward        direction from proximate the first inner conical surface (S1)        for a second length (L2) along the aerovalve longitudinal axis        (X1), the second inner diameter (D2) being less than the outer        diameter (D0); and    -   a third inner conical surface (S3) expanding radially outwardly        at a third angle (A3) to a third inner diameter (D3), the third        inner conical surface (S3) extending in the forward direction        from proximate the second inner conical surface (S2) for a third        length (L3) along the aerovalve longitudinal axis (X1), the        third inner diameter (D3) being greater than the first and        second inner diameters (D1, D2) and less than the outer diameter        (D0);        -   wherein:    -   the first angle (A1) is greater than the second angle (A2);    -   the third angle (A3) is greater than the second angle (A2); and    -   the second plurality of fuel outlet ports (2A, 2B, 2C, 2 ^(N), 2        ^(N+1)) are positioned on the third inner conical surface (S3).-   Paragraph Q: A cylindrical metal aerovalve (A) according to    Paragraph P, wherein the first angle (A1) ranges from between 30    degrees to 60 degrees.-   Paragraph R: A cylindrical metal aerovalve (A) according to    Paragraph P, wherein the second angle (A2) ranges from between 1.5    degrees to 11.25 degrees.-   Paragraph S: The cylindrical metal aerovalve (A) according to    Paragraph P, wherein the third angle (A3) ranges from between 11.25    degrees to 90 degrees.-   Paragraph T: The cylindrical metal aerovalve (A) according to    Paragraph P, wherein the total aerovalve length (L) to first inner    diameter (D1) ratio ranges from 2.5 to 10.-   Paragraph U: The cylindrical metal aerovalve (A) according to    Paragraph P, wherein the total aerovalve length (L) to outer    diameter (D0) ratio ranges from 1 to 8.-   Paragraph V: The cylindrical metal aerovalve (A) according to    Paragraph P, wherein the first inner diameter (D1) to outer diameter    (D0) ratio ranges from 1.25 to 3.75.-   Paragraph W: The pulse combustion heat exchanger (1000) according to    claim 1, wherein the mixing section comprises:    -   at least one metal aerovalve (A), having an aerovalve        longitudinal axis (X1), an outer surface (S) with an outer        diameter (D0), an interior (A-IN), a rear end (1E1) having a        rearwardly facing rear surface (1E1S), a forward end (2E1)        having a forwardly facing forward surface (2E1S), and a total        aerovalve length (L) defined between the rear and forward ends        (1E1, 2E1) along the aerovalve longitudinal axis (X1).-   Paragraph X: A metal aerovalve (A), having an aerovalve longitudinal    axis (X1), an outer surface (S) with an outer diameter (D0), an    interior (A-IN), a rear end (1E1) having a rearwardly facing rear    surface (1E1S), a forward end (2E1) having a forwardly facing    forward surface (2E1S), and a total aerovalve length (L) defined    between the rear and forward ends (1E1, 2E1) along the aerovalve    longitudinal axis (X1), the aerovalve (A) further comprising:    -   an oxidant inlet (1A0) located at the rear end (1E1), the        oxidant inlet (1A0) configured to introduce oxidant (1A1) into        the interior (A-IN) of the aerovalve (A);    -   an oxidant and fuel mixture outlet (2A0) located at the forward        end (2E1), the oxidant and fuel mixture outlet (2A0) configured        to expel an oxidant and fuel mixture (1A3) present in the        interior (A-IN) of the aerovalve (A);    -   a first plurality of fuel inlet ports (1A, 1B, 1C, 1 ^(N), 1        ^(N+1)) opening to the outer surface (S), a second plurality of        fuel outlet ports (2A, 2B, 2C, 2 ^(N), 2 ^(N+1)) opening to the        interior (A-IN), and a third plurality of fuel transfer channels        (3A, 3B, 3C, 3 ^(N), 3 ^(N+1)) configured to transfer fuel (1A2)        from the first plurality of fuel inlet ports (1A, 1B, 1C, 1        ^(N), 1 ^(N+1)) to the second plurality of fuel outlet ports        (2A, 2B, 2C, 2 ^(N), 2 ^(N+1));    -   a first inner conical surface (S1) tapering radially inwardly at        a first angle (A1) to a first inner diameter (D1), the first        inner conical surface (S1) extending in the forward direction        from proximate the rear end (1E1) for a first length (L1) along        the aerovalve longitudinal axis (X1);    -   a second inner conical surface (S2) expanding radially outwardly        at a second angle (A2) to a second inner diameter (D2), the        second inner conical surface (S2) extending in the forward        direction from proximate the first inner conical surface (S1)        for a second length (L2) along the aerovalve longitudinal axis        (X1), the second inner diameter (D2) being equal to the outer        diameter (D0), and the second length (L2) ending at the total        aerovalve length (L);    -   wherein: the first angle (A1) is greater than the second angle        (A2); and the second plurality of fuel outlet ports (2A, 2B, 2C,        2 ^(N), 2 ^(N+1)) are positioned on the second inner conical        surface (S2).-   Paragraph Y: A metal aerovalve (A), having an aerovalve longitudinal    axis (X1), an outer surface (S) with an outer diameter (D0), an    interior (A-IN), a rear end (1E1) having a rearwardly facing rear    surface (1E1S), a forward end (2E1) having a forwardly facing    forward surface (2E1S), and a total aerovalve length (L) defined    between the rear and forward ends (1E1, 2E1) along the aerovalve    longitudinal axis (X1), the aerovalve (A) further comprising:    -   an oxidant inlet (1A0) located at the rear end (1E1), the        oxidant inlet (1A0) configured to introduce oxidant (1A1) into        the interior (A-IN) of the aerovalve (A);    -   an oxidant and fuel mixture outlet (2A0) located at the forward        end (2E1), the oxidant and fuel mixture outlet (2A0) configured        to expel an oxidant and fuel mixture (1A3) present in the        interior (A-IN) of the aerovalve (A);    -   a first plurality of fuel inlet ports (1A, 1B, 1C, 1 ^(N), 1        ^(N+1)) opening to the outer surface (S), a second plurality of        fuel outlet ports (2A, 2B, 2C, 2 ^(N), 2 ^(N+1)) opening to the        interior (A-IN), and a third plurality of fuel transfer channels        (3A, 3B, 3C, 3 ^(N), 3 ^(N+1)) configured to transfer fuel (1A2)        from the first plurality of fuel inlet ports (1A, 1B, 1C, 1        ^(N), 1 ^(N+1)) to the second plurality of fuel outlet ports        (2A, 2B, 2C, 2 ^(N), 2 ^(N+1));    -   a first inner conical surface (S1) tapering radially inwardly at        a first angle (A1) to a first inner diameter (D1), the first        inner conical surface (S1) extending in the forward direction        from proximate the rear end (1E1) for a first length (L1) along        the aerovalve longitudinal axis (X1);    -   a second inner conical surface (S2) expanding radially outwardly        at a second angle (A2) to a second inner diameter (D2), the        second inner conical surface (S2) extending in the forward        direction from proximate the first inner conical surface (S1)        for a second length (L2) along the aerovalve longitudinal axis        (X1), the second inner diameter (D2) being less than the outer        diameter (D0), and the second length (L2) ending at the total        aerovalve length (L);    -   wherein: the first angle (A1) is greater than the second angle        (A2); and the second plurality of fuel outlet ports (2A, 2B, 2C,        2 ^(N), 2 ^(N+1)) are positioned on the second inner conical        surface (S2).-   Paragraph Z: A method to form a cooled combustion stream, the method    includes:    -   (a) providing a pulse combustion heat exchanger having a        longitudinal axis that includes:        -   (a1) an oxidant inlet section connected to a mixing section,            the oxidant inlet section configured to accept oxidant;        -   (a2) a fuel inlet section connected to the mixing section,            the fuel inlet section configured to accept fuel;        -   (a3) a mixing section connected to a combustion section, the            mixing section is configured to accept oxidant from the            oxidant inlet section and fuel from the fuel inlet section            and mix the oxidant with the fuel to form an oxidant and            fuel mixture;        -   (a4) a combustion section connected to a heat transfer            section, the combustion section configured to accept and            combust the oxidant and fuel mixture from the mixing section            to form a pulsating combustion stream;        -   (a5) a heat transfer section connected to a decoupler            section, the heat transfer section is configured to accept            the pulsating combustion stream from the combustion section            and cool the combustion stream by transferring heat to a            heat transfer material;        -   (a6) a decoupler section configured to acoustically            disengage the cooled combustion stream from the heat            transfer section;    -   (b) introducing oxidant to the oxidant inlet section;    -   (c) introducing fuel to the fuel inlet section;    -   (d) introducing oxidant from the oxidant inlet section to the        mixing section;    -   (e) introducing fuel from the fuel inlet section to the mixing        section;    -   (f) mixing the oxidant of step (d) with the fuel of step (e) to        form an oxidant and fuel mixture;    -   (g) introducing the oxidant and fuel mixture of step (f) into        the combustion section;    -   (h) igniting the oxidant and fuel mixture after step (g) to form        a pulsating combustion stream;    -   (i) introducing the pulsating combustion stream of step (h) into        the heat transfer section;    -   (j) transferring heat from the pulsating combustion stream after        step (i) to a heat transfer medium while cooling a portion of        the pulsating combustion stream to form a cooled combustion        stream; and    -   (k) transferring the cooled combustion stream of step (j) to the        decoupler section and acoustically disengaging the cooled        combustion stream from the heat transfer section.-   Paragraph AA: The method according the Paragraph Z, further    comprising:    -   (a) providing a first metal surface in between the combustion        section and heat transfer section; and    -   (b) contacting the first metal surface with a first coolant to        cool the first metal surface.-   Paragraph AB: The method according the Paragraph Z, wherein the    first coolant is water and heat is removed from the first metal    surface to generate a first steam.-   Paragraph AC: The method according the Paragraph AB, further    comprising:    -   (a) providing a coolant recycling drum having coolant contained        therein and having a drum outlet in fluid communication with the        first metal surface and further having drum inlet configured to        accept the first steam;    -   (b) transferring coolant from the coolant recycling drum to        contact the first metal surface;    -   (c) generating a first steam; and    -   (d) transferring the first steam to the drum inlet of the        coolant recycling drum.-   Paragraph AD: The method according the Paragraph AC, further    comprising:    -   (a) providing a first restriction orifice positioned between the        drum outlet and the first metal surface;    -   (b) prior to contacting the first metal surface with the        coolant, reducing the pressure of the coolant by passing the        coolant through the first restriction orifice.-   Paragraph AE: The method according the Paragraph AD, further    comprising:    -   (a) providing a recycling pump in between the drum outlet and        the first metal surface, the recycling pump is configured to        supply coolant under pressure to the first metal surface;    -   (b) pressurizing the coolant; and    -   (c) passing the pressurized coolant through the first        restriction orifice.-   Paragraph AF: The method according the Paragraph Z, further    comprising:    -   (a) providing a second metal surface in between the heat        transfer section and decoupler section;    -   (b) contacting the second metal surface with a second coolant to        cool the second metal surface.-   Paragraph AG: The method according the Paragraph AF, wherein the    second coolant is water and heat is removed from the second metal    surface to generate a second steam.-   Paragraph AH: The method according the Paragraph AG, further    comprising:    -   (a) providing a coolant recycling drum having coolant contained        therein and having a drum outlet in fluid communication with the        second metal surface and further having drum inlet configured to        accept the second steam;    -   (b) transferring coolant from the coolant recycling drum to        contact the second metal surface;    -   (c) generating a second steam; and    -   (d) transferring the second steam to the drum inlet of the        coolant recycling drum.-   Paragraph AI: The method according the Paragraph AH, further    comprising:    -   (a) providing a second restriction orifice positioned between        the drum outlet and the second metal surface;    -   (b) prior to contacting the second metal surface with the        coolant, reducing the pressure of the coolant by passing the        coolant through the second restriction orifice.-   Paragraph AJ: The method according the Paragraph AI, further    comprising:    -   (a) providing a recycling pump in between the drum outlet and        the second metal surface, the recycling pump is configured to        supply coolant under pressure to the second metal surface;    -   (b) pressurizing the coolant; and    -   (c) passing the pressurized coolant through the second        restriction orifice.-   Paragraph AK: The method according the Paragraph Z, further    comprising:    -   (a) providing a third metal surface in between the mixing        section and combustion section;    -   (b) contacting the third metal surface with a third coolant to        cool the third metal surface.-   Paragraph AL: The method according the Paragraph AK, wherein the    third coolant is water and heat is removed from the third metal    surface to generate a third steam.-   Paragraph AM: The method according the Paragraph AL, further    comprising:    -   (a) providing a coolant recycling drum having coolant contained        therein and having a drum outlet in fluid communication with the        third metal surface and further having drum inlet configured to        accept the third steam;    -   (b) transferring coolant from the coolant recycling drum to        contact the third metal surface;    -   (c) generating a third steam; and    -   (d) transferring the third steam to the drum inlet of the        coolant recycling drum.-   Paragraph AN: The method according the Paragraph AM, further    comprising:    -   (a) providing a third restriction orifice positioned between the        drum outlet and the third metal surface;    -   (b) prior to contacting the third metal surface with the        coolant, reducing the pressure of the coolant by passing the        coolant through the third restriction orifice.-   Paragraph AO: The method according the Paragraph AN, further    comprising:    -   (a) providing a recycling pump in between the drum outlet and        the third metal surface, the recycling pump is configured to        supply coolant under pressure to the third metal surface;    -   (b) pressurizing the coolant; and    -   (c) passing the pressurized coolant through the third        restriction orifice.-   Paragraph AP: The method according to Paragraph Z, further    comprising:    -   (a) providing a plurality of aerovalves within the mixing        section, the aerovalves have a converging-diverging geometry and        are configured to provide turbulent mixing of the oxidant and        fuel within the mixing section and minimize backflow of the        oxidant and fuel mixture from the mixing section into the        oxidant inlet section or fuel inlet section;    -   (b) subjecting the oxidant to a first drop in pressure from the        oxidant inlet section to the mixing section; and    -   (c) subjecting the fuel to a second drop in pressure from the        fuel inlet section to the mixing section.-   Paragraph AQ: The method according the Paragraph Z, further    comprising:    -   (a) providing plurality of ignitors in fluid communication with        the combustion section, each ignitor having an ignitor input        configured to introduce an ignitor mixture to the ignitor, the        ignitor input being in fluid communication with an ignitor        oxidant supply and an ignitor fuel supply;    -   (b) introducing an ignitor mixture to each of the plurality of        ignitors;    -   (c) igniting the oxidant and fuel mixture within the combustion        section with the plurality of ignitors.

BRIEF DESCRIPTION OF THE DRAWINGS

The accompanying figures show schematic process flowcharts of preferredembodiments and variations thereof. A full and enabling disclosure ofthe content of the accompanying claims, including the best mode thereofto one of ordinary skill in the art, is set forth more particularly inthe remainder of the specification, including reference to theaccompanying figures showing how the preferred embodiments and othernon-limiting variations of other embodiments described herein may becarried out in practice, in which:

FIG. 1 depicts a first embodiment of an aerovalve (A) that has two innerconical surfaces (S1, S2) and viewed from a first side cross-sectionalview (I-I).

FIG. 2 depicts the first embodiment of the aerovalve (A) as shown inFIG. 1 but viewed from a first forward view (II-II) from the forwardlyfacing forward surface (2E1S).

FIG. 3 depicts a second embodiment of an aerovalve (A) that has twoinner conical surfaces (S1, S2) and viewed from a second sidecross-sectional view (III-III).

FIG. 4 depicts the second embodiment of the aerovalve (A) as shown inFIG. 3 but viewed from a second forward view (IV-IV) from the forwardlyfacing forward surface (2E1S).

FIG. 5 depicts a third embodiment of an aerovalve (A) that has threeinner conical surfaces (S1, S2, S3) and viewed from a third sidecross-sectional view (V-V).

FIG. 6 depicts the third embodiment of the aerovalve (A) as shown inFIG. 5 but viewed from a third forward view (VI-VI) from the forwardlyfacing forward surface (2E1S).

FIG. 7 depicts one non-limiting embodiment of a pulse combustion heatexchanger (1000) that is configured to accept oxidant (1A1) and fuel(1A2) and output a cooled combustion stream (1A5), including: (a) anoxidant inlet section (100); (b) a fuel inlet section (200); (c) amixing section (300); (d) a combustion section (400); (e) a heattransfer section (500); and (f) a decoupler section (600), wherein theheat transfer section (500) is configured to transfer heat to an energysink (V108).

FIG. 8 depicts a zoomed-in view of a pulse combustion heat exchanger(1000) oxidant inlet section (100), fuel inlet section (200), mixingsection (300), combustion section (400), and a first portion of the heattransfer section (500), wherein one aerovalve (A) is positioned inbetween the oxidant inlet section (100) and the combustion section (400)and one ignitor (410) is positioned in the combustion section (400).

FIG. 9 shows one non-limiting embodiment of a combustion sectionside-view (IX-IX) that depicts a plurality of apertures (404, 404A,404B, 404 ^(N), 404 ^(N+1)) within the combustion section (400)tubesheet (403) and a plurality of resonance conduits (502, 502A, 502B,502C, 502D, 502E, 502 ^(N), 502 ^(N+1)) are positioned within theplurality of apertures (404, 404A, 404B, 404 ^(N), 404 ^(N+1)).

FIG. 10 shows a zoomed-in view of a pulse combustion heat exchanger(1000) oxidant inlet section (100), fuel inlet section (200), mixingsection (300), combustion section (400), and a first portion of the heattransfer section (500) wherein a plurality of aerovalves (A, A′) arepositioned in between the oxidant inlet section (100) and the combustionsection (400) and one ignitor (410) is positioned in the mixing section(300).

FIG. 11 shows one non-limiting embodiment of an oxidant inlet sectionside-view (XI-XI) that depicts a plurality of aerovalves (A, A′, A″,A′″, A^(N), A^(N+1)) inserted into a plurality of aerovalve apertures(106, 106A, 106B, 106C, 106D, 106 ^(N), 106 ^(N+1)) within the oxidantinlet section (100) tubesheet (104A), also showing an ignitor aperture(410A2, 410A21) positioned in the tubesheet (104A) for insertion of anignitor (410) through the tubesheet (104A) into the mixing section(300), and also showing a plurality of apertures (110A, 110B) in thetubesheet (104A) for introducing oxidant (1A1) into the mixing section(300).

FIG. 12 elaborates upon the oxidant inlet section side-view (XI-XI)disclosure of FIG. 11 however showing the oxidant inlet section (100)tubesheet (104A) having 33 aerovalves (A, A′, A″, A′″, A^(N), A^(N+1)),and 4 ignitor apertures (410A21, 410A22, 410A23, 410A24) that areconfigured to have a plurality of ignitors (410A, 410B, 410C, 410D)inserted into.

FIG. 13 shows a zoomed-in view of a pulse combustion heat exchanger(1000) oxidant inlet section (100), fuel inlet section (200), mixingsection (300), combustion section (400), and a first portion of the heattransfer section (500) wherein one aerovalve (A) is positioned inbetween the oxidant inlet section (100) and the combustion section(400), and a third transition section (350) is positioned between themixing section (300) and the combustion section (400) and is providedwith a third coolant (351).

FIG. 14 elaborates upon the non-limiting embodiment of FIG. 13 and showsa first transition section (450) configured to cool in between thecombustion section (400) and the heat transfer section (500) via acoolant inlet (452) and a coolant outlet (454).

FIG. 15 elaborates upon the non-limiting embodiment of FIGS. 10, 13, and14 and shows a plurality of aerovalves (A, A′) positioned in between theoxidant inlet section (100) and the combustion section (400), a firsttransition section (450) positioned between the combustion section (400)and the heat transfer section (500) that is provided with a firstcoolant (451), and a third transition section (350) is positionedbetween the mixing section (300) and the combustion section (400) and isprovided with a third coolant (351).

FIG. 16 elaborates upon the non-limiting embodiment of FIG. 15 and showsthe fuel inlet section (200) contained within at least one fuel injector(370A, 370B), the fuel injector (370A, 370B) is comprised of a fuelinjector conduit (372A, 372B) connected to a fuel injector distributor(374A, 374B), the fuel injector conduit (372A, 372B) is configured toaccept fuel (1A2), and the fuel injector distributor (374A, 374B) isconfigured to transfer the fuel (1A2) from the fuel injector conduit(372A, 372B) into the mixing section (300).

FIG. 17 shows one non-limiting embodiment of a pulse combustion heatexchanger (1000) that is configured to accept oxidant (1A1) and fuel(1A2) and output a cooled combustion stream (1A5).

FIG. 18 elaborates upon the non-limiting embodiment of FIG. 17 howeverdepicts the mixing section (300) with a plurality of aerovalves (A, A′,A″).

FIG. 19 depicts one non-limiting embodiment of a vessel (V100) equippedwith a first pulse combustion heat exchanger (1000A) and a second pulsecombustion heat exchanger (1000B), the first pulse combustion heatexchanger (1000A) has a first flange (PC1A) that is connected to a firstvessel flange (V1F) and a second flange (PC2A) that is connected to asecond vessel flange (V2F), and the second pulse combustion heatexchanger (1000B) has a first flange (PC1B) that is connected to a thirdvessel flange (V3F) and a second flange (PC2B) that is connected to afourth vessel flange (V4F).

FIG. 20 depicts a pulse combustion heat exchanger (1000) having a firsttransition section (450) with a first coolant inlet (452) and a firstcoolant outlet (454), a second transition section (650) with a secondcoolant inlet (652) and a second coolant outlet (654), a thirdtransition section (350) with a third coolant inlet (352) and a thirdcoolant outlet (354), and a coolant recycling drum (800) in fluidcommunication with the first coolant inlet (452), the second coolantinlet (652), and the third coolant inlet (352) via a coolant transferconduit (817).

FIG. 21 elaborates upon the non-limiting embodiment of FIG. 20 includinga recycling pump (810) interposed on the coolant transfer conduit (817)to pressurize the coolant (818) provided by the coolant recycling drum(800) and provide a source of pressurized coolant (815) to the firstcoolant inlet (452), the second coolant inlet (652), and the thirdcoolant inlet (352).

FIG. 22 discloses a method to form a cooled combustion stream.

DETAILED DESCRIPTION

Reference will now be made in detail to various embodiments of thedisclosure. Each embodiment is provided by way of explanation of thedisclosure, not limitation of the disclosure. In fact, it will beapparent to those skilled in the art that modifications and variationscan be made in the disclosure without departing from the teaching andscope thereof. For instance, features illustrated or described as partof one embodiment to yield a still further embodiment derived from theteaching of the disclosure. Thus, it is intended that the disclosure orcontent of the claims cover such derivative modifications and variationsto come within the scope of the disclosure or claimed embodimentsdescribed herein and their equivalents.

Additional objects and advantages of the disclosure will be set forth inpart in the description which follows, and in part will be obvious fromthe description, or may be learned by practice of the claims. Theobjects and advantages of the disclosure will be attained by means ofthe instrumentalities and combinations and variations particularlypointed out in the appended claims.

FIG. 1

FIG. 1 depicts a first embodiment of an aerovalve (A) that has two innerconical surfaces (S1, S2) and viewed from a first side cross-sectionalview (I-I).

FIG. 1 discloses a metal aerovalve (A), having an aerovalve longitudinalaxis (X1), an outer surface (S) with an outer diameter (D0), an interior(A-IN), a rear end (1E1) having a rearwardly facing rear surface (1E1S),a forward end (2E1) having a forwardly facing forward surface (2E1S),and a total aerovalve length (L) defined between the rear and forwardends (1E1, 2E1) along the aerovalve longitudinal axis (X1), theaerovalve (A) further comprising:

-   -   an oxidant inlet (1A0) located at the rear end (1E1), the        oxidant inlet (1A0) configured to introduce oxidant (1A1) into        the interior (A-IN) of the aerovalve (A);    -   an oxidant and fuel mixture outlet (2A0) located at the forward        end (2E1), the oxidant and fuel mixture outlet (2A0) configured        to expel an oxidant and fuel mixture (1A3) present in the        interior (A-IN) of the aerovalve (A);    -   a first plurality of fuel inlet ports (1A, 1B, 1 ^(N), 1 ^(N+1))        opening to the outer surface (S), a second plurality of fuel        outlet ports (2A, 2B, 2C, 2D, 2E, 2F, 2G, 2 ^(N), 2 ^(N+1))        opening to the interior (A-IN), and a third plurality of fuel        transfer channels (3A, 3B, 3 ^(N), 3 ^(N+1)) configured to        transfer fuel (1A2) from the first plurality of fuel inlet ports        (1A, 1B, 1 ^(N), 1 ^(N+1)) to the second plurality of fuel        outlet ports (2A, 2B, 2C, 2D, 2E, 2F, 2G, 2 ^(N), 2 ^(N+1));    -   a first inner conical surface (S1) tapering radially inwardly at        a first angle (A1) to a first inner diameter (D1), the first        inner conical surface (S1) extending in the forward direction        from proximate the rear end (1E1) for a first length (L1) along        the aerovalve longitudinal axis (X1);    -   a second inner conical surface (S2) expanding radially outwardly        at a second angle (A2) to a second inner diameter (D2), the        second inner conical surface (S2) extending in the forward        direction from proximate the first inner conical surface (S1)        for a second length (L2) along the aerovalve longitudinal axis        (X1), the second inner diameter (D2) being equal to the outer        diameter (D0), and the second length (L2) ending at the total        aerovalve length (L).

FIG. 1 shows the first angle (A1) greater than the second angle (A2) andthe second plurality of fuel outlet ports (2A, 2B, 2C, 2D, 2E, 2F, 2G, 2^(N), 2 ^(N+1)) are positioned on the second inner conical surface (S2).

FIG. 1 also shows that the first plurality of fuel inlet ports (1A, 1B,1 ^(N), 1 ^(N+1)) and a second plurality of fuel outlet ports (2A, 2B,2C, 2E, 2F, 2G, 2 ^(N), 2 ^(N+1)) both located at a fourth length (L4)that is positioned extending in the forward direction from proximate therear end (1E1) along the aerovalve longitudinal axis (X1). The fueltransfer channels (3A, 3B, 3 ^(N), 3 ^(N+1)) have a channel diameter(XX1) and are configured to transfer fuel from the first plurality offuel inlet ports (1A, 1B, 1 ^(N), 1 ^(N+1)) to the second plurality offuel outlet ports (2A, 2B, 2C, 2E, 2F, 2G, 2 ^(N), 2 ^(N+1)). Theinterior (A-IN) of the aerovalve (A) may be considered as a mixingsection (300).

In embodiments, the first angle (A1) ranges from between 30 degrees to60 degrees. In embodiments, the second angle (A2) ranges from between1.5 degrees to 11.25 degrees. In embodiments, the total aerovalve length(L) to first inner diameter (D1) ratio ranges from 2.5 to 10. Inembodiments, the total aerovalve length (L) to outer diameter (D0) ratioranges from 1 to 8. In embodiments, the first inner diameter (D1) toouter diameter (D0) ratio ranges from 1.25 to 3.75.

FIG. 2

FIG. 2 depicts the first embodiment of the aerovalve (A) as shown inFIG. 1 but viewed from a first forward view (II-II) from the forwardlyfacing forward surface (2E1S).

The first forward view (II-II) of FIG. 2 views the aerovalve (A) fromthe forwardly facing forward surface (2E1S). The second inner conicalsurface (S2) is visible in FIG. 2 since the aerovalve (A) is depictedfrom the oxidant and fuel mixture outlet (2A0) at the forward end (2E1).

FIG. 2 shows a plurality of fuel inlet ports (1A, 1B, 1C, 1D, 1E, 1F,1G, 1H, 1I, 1J, 1K, 1L) opening to the outer surface (S), a secondplurality of fuel outlet ports (2A, 2B, 2C, 2D, 2E, 2F, 2G, 2H, 2I, 2J,2K, 2L) opening to the interior (A-IN), and a third plurality of fueltransfer channels (3A, 3B, 3C, 3D, 3E, 3F, 3G, 3H, 3I, 3J, 3K, 3L)configured to transfer fuel (1A2) from the first plurality of fuel inletports (1A, 1B, 1C, 1D, 1E, 1F, 1G, 1H, 1I, 1J, 1K, 1L) to the secondplurality of fuel outlet ports (2A, 2B, 2C, 2D, 2E, 2F, 2G, 2H, 2I, 2J,2K, 2L).

FIG. 2 also shows the second inner conical surface (S2) expandingradially outward from the first inner diameter (D1) to the second innerdiameter (D2). FIG. 2 shows the second inner diameter (D2) equal to theouter diameter (D0).

FIG. 3

FIG. 3 depicts a second embodiment of an aerovalve (A) that has twoinner conical surfaces (S1, S2) and viewed from a second sidecross-sectional view (III-III).

FIG. 3 discloses a metal aerovalve (A), having an aerovalve longitudinalaxis (X1), an outer surface (S) with an outer diameter (D0), an interior(A-IN), a rear end (1E1) having a rearwardly facing rear surface (1E1S),a forward end (2E1) having a forwardly facing forward surface (2E1S),and a total aerovalve length (L) defined between the rear and forwardends (1E1, 2E1) along the aerovalve longitudinal axis (X1), theaerovalve (A) further comprising:

-   -   an oxidant inlet (1A0) located at the rear end (1E1), the        oxidant inlet (GAO) configured to introduce oxidant (1A1) into        the interior (A-IN) of the aerovalve (A);    -   an oxidant and fuel mixture outlet (2A0) located at the forward        end (2E1), the oxidant and fuel mixture outlet (2A0) configured        to expel an oxidant and fuel mixture (1A3) present in the        interior (A-IN) of the aerovalve (A);    -   a first plurality of fuel inlet ports (1A, 1B, 1 ^(N), 1 ^(N+1))        opening to the outer surface (S), a second plurality of fuel        outlet ports (2A, 2B, 2C, 2D, 2E, 2F, 2G, 2 ^(N), 2 ^(N+1)))        opening to the interior (A-IN), and a third plurality of fuel        transfer channels (3A, 3B, 3 ^(N), 3 ^(N+1)) configured to        transfer fuel (1A2) from the first plurality of fuel inlet ports        (1A, 1B, 1C, 1 ^(N), 1 ^(N+1)) to the second plurality of fuel        outlet ports (2A, 2B, 2C, 2D, 2E, 2F, 2G, 2 ^(N), 2 ^(N+1));    -   a first inner conical surface (S1) tapering radially inwardly at        a first angle (A1) to a first inner diameter (D1), the first        inner conical surface (S1) extending in the forward direction        from proximate the rear end (1E1) for a first length (L1) along        the aerovalve longitudinal axis (X1);    -   a second inner conical surface (S2) expanding radially outwardly        at a second angle (A2) to a second inner diameter (D2), the        second inner conical surface (S2) extending in the forward        direction from proximate the first inner conical surface (S1)        for a second length (L2) along the aerovalve longitudinal axis        (X1), the second inner diameter (D2) being less than the outer        diameter (D0), and the second length (L2) ending at the total        aerovalve length (L).

The first angle (A1) is greater than the second angle (A2) and thesecond plurality of fuel outlet ports (2A, 2B, 2C, 2 ^(N), 2 ^(N+1)) arepositioned on the second inner conical surface (S2). In embodiments, thefirst angle (A1) ranges from between 30 degrees to 60 degrees. Inembodiments, the second angle (A2) ranges from between 1.5 degrees to11.25 degrees. In embodiments, the total aerovalve length (L) to firstinner diameter (D1) ratio ranges from 2.5 to 10. In embodiments, thetotal aerovalve length (L) to outer diameter (D0) ratio ranges from 1 to8. In embodiments, the first inner diameter (D1) to outer diameter (D0)ratio ranges from 1.25 to 3.75.

FIG. 3 also shows the first plurality of fuel inlet ports (1A, 1B, 1^(N), 1 ^(N+1)) located at a fourth length (L4) that is positionedextending in the forward direction from proximate the rear end (1E1)along the aerovalve longitudinal axis (X1). FIG. 3 also shows thatsecond plurality of fuel outlet ports (2A, 2B, 2C, 2E, 2F, 2G, 2 ^(N), 2^(N+1)) located at a fifth length (L5) that is positioned extending inthe forward direction from proximate the rear end (1E1) along theaerovalve longitudinal axis (X1). The fuel transfer channels (3A, 3B, 3^(N), 3 ^(N+1)) have a channel diameter (XX1) and sixth length (L6) thatis the difference between the fourth length (L4) and fifth length (L5).The interior (A-IN) of the aerovalve (A) may be considered as a mixingsection (300).

FIG. 4

FIG. 4 depicts the second embodiment of the aerovalve (A) as shown inFIG. 3 but viewed from a second forward view (IV-IV) from the forwardlyfacing forward surface (2E1S).

The second forward view (IV-IV) of FIG. 4 views the aerovalve (A) fromthe forwardly facing forward surface (2E1S). The second inner conicalsurface (S2) is visible in FIG. 4 since the aerovalve (A) is depictedfrom the oxidant and fuel mixture outlet (2A0) at the forward end (2E1).

FIG. 4 shows a plurality of fuel inlet ports (1A, 1B, 1C, 1D, 1E, 1F,1G, 1H, 1I, 1J, 1K, 1L) opening to the outer surface (S), a secondplurality of fuel outlet ports (2A, 2B, 2C, 2D, 2E, 2F, 2G, 2H, 2I, 2J,2K, 2L) opening to the interior (A-IN), and a third plurality of fueltransfer channels (3A, 3B, 3C, 3D, 3E, 3F, 3G, 3H, 3I, 3J, 3K, 3L)configured to transfer fuel (1A2) from the first plurality of fuel inletports (1A, 1B, 1C, 1D, 1E, 1F, 1G, 1H, 1I, 1J, 1K, 1L) to the secondplurality of fuel outlet ports (2A, 2B, 2C, 2D, 2E, 2F, 2G, 2H, 2I, 2J,2K, 2L).

FIG. 4 also shows the second inner conical surface (S2) expandingradially outwardly from the first inner diameter (D1) to the secondinner diameter (D2). FIG. 4 shows the second inner diameter (D2) lessthan the outer diameter (D0).

FIG. 5

FIG. 5 depicts a third embodiment of an aerovalve (A) that has threeinner conical surfaces (S1, S2, S3) and viewed from a third sidecross-sectional view (V-V).

FIG. 5 discloses a metal aerovalve (A), having an aerovalve longitudinalaxis (X1), an outer surface (S) with an outer diameter (D0), an interior(A-IN), a rear end (1E1) having a rearwardly facing rear surface (1E1S),a forward end (2E1) having a forwardly facing forward surface (2E1S),and a total aerovalve length (L) defined between the rear and forwardends (1E1, 2E1) along the aerovalve longitudinal axis (X1), theaerovalve (A) further comprising:

-   -   an oxidant inlet (1A0) located at the rear end (1E1), the        oxidant inlet (1A0) configured to introduce oxidant (1A1) into        the interior (A-IN) of the aerovalve (A);    -   an oxidant and fuel mixture outlet (2A0) located at the forward        end (2E1), the oxidant and fuel mixture outlet (2A0) configured        to expel an oxidant and fuel mixture (1A3) present in the        interior (A-IN) of the aerovalve (A);    -   a first plurality of fuel inlet ports (1A, 1B, 1 ^(N), 1 ^(N+1))        opening to the outer surface (S), a second plurality of fuel        outlet ports (2A, 2B, 2C, 2D, 2E, 2F, 2G, 2 ^(N), 2 ^(N+1))        opening to the interior (A-IN), and a third plurality of fuel        transfer channels (3A, 3B, 3 ^(N), 3 ^(N+1)) configured to        transfer fuel (1A2) from the first plurality of fuel inlet ports        (1A, 1B, 1 ^(N), 1 ^(N+1)) to the second plurality of fuel        outlet ports (2A, 2B, 2C, 2D, 2E, 2F, 2G, 2 ^(N), 2 ^(N));    -   a first inner conical surface (S1) tapering radially inwardly at        a first angle (A1) to a first inner diameter (D1), the first        inner conical surface (S1) extending in the forward direction        from proximate the rear end (1E1) for a first length (L1) along        the aerovalve longitudinal axis (X1);    -   a second inner conical surface (S2) expanding radially outwardly        at a second angle (A2) to a second inner diameter (D2), the        second inner conical surface (S2) extending in the forward        direction from proximate the first inner conical surface (S1)        for a second length (L2) along the aerovalve longitudinal axis        (X1), the second inner diameter (D2) being less than the outer        diameter (D0); and    -   a third inner conical surface (S3) expanding radially outwardly        at a third angle (A3) to a third inner diameter (D3), the third        inner conical surface (S3) extending in the forward direction        from proximate the second inner conical surface (S2) for a third        length (L3) along the aerovalve longitudinal axis (X1), the        third inner diameter (D3) being greater than the first and        second inner diameters (D1, D2) and less than the outer diameter        (D0);

The first angle (A1) is greater than the second angle (A2), the thirdangle (A3) is greater than the second angle (A2), and the secondplurality of fuel outlet ports (2A, 2B, 2C, 2 ^(N), 2 ^(N+1)) arepositioned on the third inner conical surface (S3).

FIG. 5 also shows the first plurality of fuel inlet ports (1A, 1B, 1^(N), 1 ^(N+1)) located at a fourth length (L4) that is positionedextending in the forward direction from proximate the rear end (1E1)along the aerovalve longitudinal axis (X1). FIG. 5 also shows thatsecond plurality of fuel outlet ports (2A, 2B, 2C, 2E, 2F, 2G, 2 ^(N), 2^(N+1)) located at a fifth length (L5) that is positioned extending inthe forward direction from proximate the rear end (1E1) along theaerovalve longitudinal axis (X1). The fuel transfer channels (3A, 3B, 3^(N), 3 ^(N+1)) have a channel diameter (XX1) and sixth length (L6) thatis the difference between the fourth length (L4) and fifth length (L5).The interior (A-IN) of the aerovalve (A) may be considered as a mixingsection (300).

In embodiments, the first angle (A1) ranges from between 30 degrees to60 degrees. In embodiments, the second angle (A2) ranges from between1.5 degrees to 11.25 degrees. In embodiments, the third angle (A3)ranges from between 11.25 degrees to 90 degrees. In embodiments, thetotal aerovalve length (L) to first inner diameter (D1) ratio rangesfrom 2.5 to 10. In embodiments, the total aerovalve length (L) to outerdiameter (D0) ratio ranges from 1 to 8. In embodiments, the first innerdiameter (D1) to outer diameter (D0) ratio ranges from 1.25 to 3.75.

FIG. 6

FIG. 6 depicts the third embodiment of the aerovalve (A) as shown inFIG. 5 but viewed from a third forward view (VI-VI) from the forwardlyfacing forward surface (2E1S).

The third forward view (VI-VI) of FIG. 6 views the aerovalve (A) fromthe forwardly facing forward surface (2E1S). The second inner conicalsurface (S2) and third inner conical surface (S3) are both visible inFIG. 6 since the aerovalve (A) is depicted from the oxidant and fuelmixture outlet (2A0) at the forward end (2E1).

FIG. 6 shows a plurality of fuel inlet ports (1A, 1B, 1C, 1D, 1E, 1F,1G, 1H, 1I, 1J, 1K, 1L) opening to the outer surface (S), a secondplurality of fuel outlet ports (2A, 2B, 2C, 2D, 2E, 2F, 2G, 2H, 2I, 2J,2K, 2L) opening to the interior (A-IN), and a third plurality of fueltransfer channels (3A, 3B, 3C, 3D, 3E, 3F, 3G, 3H, 3I, 3J, 3K, 3L)configured to transfer fuel (1A2) from the first plurality of fuel inletports (1A, 1B, 1C, 1D, 1E, 1F, 1G, 1H, 1I, 1J, 1K, 1L) to the secondplurality of fuel outlet ports (2A, 2B, 2C, 2D, 2E, 2F, 2G, 2H, 2I, 2J,2K, 2L).

FIG. 6 also shows the second inner conical surface (S2) expandingradially outwardly from the first inner diameter (D1) to the secondinner diameter (D2) and the third inner conical surface (S3) expandingradially outwardly to a third inner diameter (D3). FIG. 6 shows thethird inner diameter (D3) less than the outer diameter (D0).

FIG. 7

FIG. 7 depicts one non-limiting embodiment of a pulse combustion heatexchanger (1000) that is configured to accept oxidant (1A1) and fuel(1A2) and output a cooled combustion stream (1A5), including: (a) anoxidant inlet section (100); (b) a fuel inlet section (200); (c) amixing section (300); (d) a combustion section (400); (e) a heattransfer section (500); and (f) a decoupler section (600), wherein theheat transfer section (500) is configured to transfer heat to an energysink (V108).

FIG. 7 depicts a one non-limiting embodiment of a pulse combustion heatexchanger (1000) having an exchanger longitudinal axis (X2) that isconfigured to accept oxidant (1A1) and fuel (1A2) and output a cooledcombustion stream (1A5). The pulse combustion heat exchanger (1000) ofFIG. 7 has an oxidant inlet section (100) that is configured to acceptoxidant (1A1), a fuel inlet section (200) that is configured to acceptfuel (1A2), a mixing section (300) including one aerovalve (A) that isconfigured to accept and mix oxidant (1A1) from the oxidant inletsection (100) with fuel (1A2) from the fuel inlet section (200) tocreate an oxidant and fuel mixture (1A3), a combustion section (400)configured to receive and combust the oxidant and fuel mixture (1A3)from the mixing section (300) to produce a pulsating combustion stream(1A4), a heat transfer section (500) configured to receive thecombustion stream (1A4) from the combustion section (400), the heattransfer section (500) including one resonance conduit (502) that isconfigured to transfer heat from the combustion stream (1A4) to anenergy sink (V108), and a decoupler section (600) connected to the heattransfer section (500) and configured to accept a cooled combustionstream (1A5) from the heat transfer section (500) and output the cooledcombustion stream (1A5) via a combustion stream outlet (606). Inembodiments, combustion of the oxidant and fuel mixture (1A3) maycontinue to take place within the heat transfer section (500). Inembodiments, at least a portion of the pulsating combustion stream (1A4)is cooled in the heat transfer section (500) to form a cooled combustionstream (1A5).

In embodiments, the vessel (V100) has an interior (V102) defined by atleast one side wall (V104) with a heat transfer medium (V106) containedwithin the interior (V102). In embodiments, the heat transfer medium(V106) serves as an energy sink (V108). In embodiments, the heattransfer medium (V106) may be a solid, liquid, or gas or mixturesthereof. In embodiments, the heat transfer medium (V106) may includeparticulates.

In embodiments, the vessel (V100) is equipped with an inlet (V110) andan outlet (V112). In embodiments, the inlet (V110) has a mass input(V111) for accepting a substance such as a solid, liquid, or gas to theinterior (V102) of the vessel (V100). In embodiments, the outlet (V112)has a mass output (V113) that is configured to discharge a substancesuch as a solid, liquid, or gas from the interior (V102) of the vessel(V100).

FIG. 7 also depicts one non-limiting embodiment of a vessel (V100)equipped with a pulse combustion heat exchanger (1000). The pulsecombustion heat exchanger (1000) has a first flange (PC1A) that isconnected to a first vessel flange (V1F) and a second flange (PC2A) thatis connected to a second vessel flange (V2F).

Oxidant (1A1) is introduced into the oxidant inlet section (100) via anoxidant inlet (102). The oxidant inlet section (100) has an interiorthat is defined by a first plate (103) and a second plate (104). Theoxidant inlet (102) is interposed in the first plate (103) and isconfigured to transfer oxidant (1A1) into the interior of the oxidantinlet section (100). Oxidant (1A1) is transferred from the oxidant inletsection (100) into the aerovalve (A) via an aerovalve aperture (106).Oxidant (1A1) is mixed with fuel (1A2) within the interior of theaerovalve (A) to form an oxidant and fuel mixture (1A3).

Fuel (1A2) is transferred into the fuel inlet section (200) via a fuelinlet (202). The fuel inlet (202) passes through the first plate (103)of the oxidant inlet section (100) via a first fuel aperture (108) andthen through the second plate (104) of the oxidant inlet section (100)into the fuel inlet section (200) via a second fuel aperture (110). Thefuel inlet section (200) has an interior that is defined by the secondplate (104) and the third plate (204).

The oxidant (1A1) and fuel (1A2) mix within the mixing section (300)within the aerovalve (A) and form an oxidant and fuel mixture (1A3). Theoxidant and fuel mixture (1A3) is transferred from the mixing section(300) into the combustion section (400) where it is ignited to form apulsating combustion stream (1A4). In embodiments, the oxidant and fuelmixture (1A3) is ignited in the mixing section (300) to form a pulsatingcombustion stream (1A4).

The combustion section (400) has an interior that is defined by thethird plate (204) and a fourth plate (402). The fourth plate has anaperture (404) within it that one resonance conduit (502) is showninserted into. The combustion section (400) has a first refractorysection (406) that is positioned within the interior of the combustionsection (400) and connected to the third plate (204).

The resonance conduit (502) defines the heat transfer section (500). Theheat transfer section (500) is connected to the decoupler section (600).The decoupler section (600) has an interior that is defined by a fifthplate (602) and a combustion stream outlet (606). The fifth plate (602)has an aperture (604) within it that the resonance conduit (502) isinserted into. Heat from the combustion stream (1A4) is transferredthrough the wall of the resonance conduit (502) into the heat transfermedium (V106) within the interior (V102) of the vessel (V100).

In embodiments, the decoupler section (600) accepts a cooled combustionstream (1A5) from the heat transfer section (500). The cooled combustionstream (1A5) is evacuated from the decoupler section (600) via acombustion stream outlet (606). The decoupler section (600) isconfigured to acoustically disengage the cooled combustion stream (1A5)from the heat transfer section (500).

FIG. 8

FIG. 8 depicts a zoomed-in view of a pulse combustion heat exchanger(1000) oxidant inlet section (100), fuel inlet section (200), mixingsection (300), combustion section (400), and a first portion of the heattransfer section (500), wherein one aerovalve (A) is positioned inbetween the oxidant inlet section (100) and the combustion section (400)and one ignitor (410) is positioned in the combustion section (400).

FIG. 8 also depicts one non-limiting embodiment of a vessel (V100)equipped with a pulse combustion heat exchanger (1000). The pulsecombustion heat exchanger (1000) has a first flange (PC1) that isconnected to a first vessel flange (V1F).

Oxidant (1A1) is introduced into the oxidant inlet section (100) via anoxidant inlet (102). The oxidant inlet section (100) has an interiorthat is defined by a first plate (103) and a second plate (104). Theoxidant inlet (102) is interposed in the first plate (103) and isconfigured to transfer oxidant (1A1) into the interior of the oxidantinlet section (100). Oxidant (1A1) is transferred from the oxidant inletsection (100) into the aerovalve (A) via an aerovalve aperture (106).Oxidant (1A1) is mixed with fuel (1A2) within the interior of theaerovalve (A) to form an oxidant and fuel mixture (1A3).

Fuel (1A2) is transferred into the fuel inlet section (200) via a fuelinlet (202). The fuel inlet (202) passes through the first plate (103)of the oxidant inlet section (100) via a first fuel aperture (108) andthen through the second plate (104) of the oxidant inlet section (100)into the fuel inlet section (200) via a second fuel aperture (110). Thefuel inlet section (200) has an interior that is defined by the secondplate (104) and the third plate (204).

The oxidant (1A1) and fuel (1A2) mix within the mixing section (300)within the aerovalve (A) and form an oxidant and fuel mixture (1A3). Theoxidant and fuel mixture (1A3) is transferred from the mixing section(300) into the combustion section (400) where it is ignited to form apulsating combustion stream (1A4).

The combustion section (400) has an interior that is defined by thethird plate (204) and a fourth plate (402). The fourth plate has aplurality of apertures (404, 404A, 404B, 404C, 404D, 404E) within iteach having a resonance conduit (502A, 502B, 502C, 502D, 502E) insertedinto. The combustion section (400) has a second refractory section (408)that is positioned within the interior of the combustion section (400)and connected to the fourth plate (402).

In embodiments, the fourth plate (402) may be a tubesheet (403) having aplurality of apertures (404, 404A, 404B, 404C, 404D, 404E) for which aplurality of resonance conduits (502A, 502B, 502C, 502D, 502E) are showninserted into.

The plurality of resonance conduits (502A, 502B, 502C, 502D, 502E)define the heat transfer section (500). The heat transfer section (500)is connected to the decoupler section (600). The decoupler section (600)has an interior that is defined by a fifth plate (602) and a combustionstream outlet (606). The fifth plate (602) has a plurality of apertures(604A, 604B, 604C, 604D) within it that the plurality of resonanceconduits (502A, 502B, 502C, 502D, 502E) are inserted into (See FIG. 17).

FIG. 8 shows one ignitor (410) positioned in the combustion section(400) and in fluid communication with the mixing section (400). Theignitor (410) is configured to ignite the oxidant and fuel mixture (1A3)to create a pulsating combustion stream (1A4). An ignitor mixture (1A6)is made available to the ignitor (410) via an ignitor input (412). Theignitor mixture (1A6) is a mixture of fuel and oxidant that is providedby an ignitor fuel supply and an ignitor oxidant supply. FIG. 8 showsthe ignitor (410) extending into the combustion section (400) by passingthrough the first, second, and third plates (103, 104, 204). The firstplate (103) has a first ignitor aperture (410A1), the second plate (104)has a second ignitor aperture (410A2), and the third plate has a thirdignitor aperture (410A3).

Reference numerals (IX-IX) in FIG. 8 depict the combustion sectionside-view that is elaborated upon in FIG. 9.

FIG. 9

FIG. 9 shows one non-limiting embodiment of a combustion sectionside-view (IX-IX) that depicts a plurality of apertures (404, 404A,404B, 404 ^(N), 404 ^(N+1)) within the combustion section (400)tubesheet (403) and a plurality of resonance conduits (502, 502A, 502B,502C, 502D, 502E, 502 ^(N), 502 ^(N+1)) are positioned within theplurality of apertures (404, 404A, 404B, 404 ^(N), 404 ^(N+1)).

FIG. 10

FIG. 10 shows a zoomed-in view of a pulse combustion heat exchanger(1000) oxidant inlet section (100), fuel inlet section (200), mixingsection (300), combustion section (400), and a first portion of the heattransfer section (500) wherein a plurality of aerovalves (A, A′) arepositioned in between the oxidant inlet section (100) and the combustionsection (400) and one ignitor (410) is positioned in the mixing section(300).

FIG. 10 depicts one non-limiting embodiment of a vessel (V100) equippedwith a pulse combustion heat exchanger (1000). The pulse combustion heatexchanger (1000) has a first flange (PC1) that is connected to a firstvessel flange (V1F).

Oxidant (1A1) is introduced into the oxidant inlet section (100) via anoxidant inlet (102). The oxidant inlet section (100) has an interiorthat is defined by a first plate (103) and a second plate (104). Theoxidant inlet (102) is interposed in the first plate (103) and isconfigured to transfer oxidant (1A1) into the interior of the oxidantinlet section (100). Oxidant (1A1) is transferred from the oxidant inletsection (100) into the plurality of aerovalves (A, A′) via a pluralityof aerovalve apertures (106A, 106B). Oxidant (1A1) is mixed with fuel(1A2) within the interior of the plurality of aerovalves (A, A′) to forman oxidant and fuel mixture (1A3). The interior of the plurality ofaerovalves (A, A′) is considered the mixing section (300) of the pulsecombustion heat exchanger (1000).

Fuel (1A2) is transferred into the fuel inlet section (200) via a firstfuel inlet (202A) and a second fuel inlet (202B). The plurality fuelinlets (202A, 202B) pass through the first plate (103) of the oxidantinlet section (100) via a plurality of first fuel apertures (108A,108B). The plurality fuel inlets (202A, 202B) pass through the firstplate (103) of the oxidant inlet section (100) via a first first fuelaperture (108A) and a second first fuel aperture (108B). The pluralityfuel inlets (202A, 202B) then pass through the second plate (104) of theoxidant inlet section (100) via a plurality of second fuel apertures(110A, 110B). The plurality fuel inlets (202A, 202B) then pass throughthe second plate (104) of the oxidant inlet section (100) via a firstsecond fuel aperture (110A) and a second second fuel aperture (110B).The fuel inlet section (200) has an interior that is defined by thesecond plate (104) and the third plate (204).

The oxidant (1A1) and fuel (1A2) mix within the mixing section (300)within the aerovalves (A, A′) and form an oxidant and fuel mixture(1A3). The oxidant and fuel mixture (1A3) are ignited in the mixingsection (300) to form a pulsating combustion stream (1A4). Thecombustion section (400) has an interior that is defined by the thirdplate (204) and a fourth plate (402). The fourth plate has a pluralityof apertures (404, 404A, 404B, 404C, 404D, 404E, 404 ^(N), 404 ^(N+1))within it each having a resonance conduit (502A, 502B, 502C, 502D, 502E,502 ^(N), 502 ^(N+1)) inserted into. The combustion section (400) has asecond refractory section (408) that is positioned within the interiorof the combustion section (400) and connected to the fourth plate (402).In embodiments, the fourth plate (402) may be a tubesheet (403) having aplurality of apertures (404, 404A, 404B, 404C, 404D, 404E, 404 ^(N), 404^(N+1)) for which a plurality of resonance conduit (502A, 502B, 502C,502D, 502E, 502 ^(N), 502 ^(N+1)) are shown inserted into. The pluralityof resonance conduits (502A, 502B, 502C, 502D, 502E, 502 ^(N), 502^(N+1)) define the heat transfer section (500). The heat transfersection (500) is connected to the decoupler section (600).

FIG. 10 shows one ignitor (410) positioned in the mixing section (300)and in fluid communication with the combustion section (400). Theignitor (410) is configured to ignite the oxidant and fuel mixture (1A3)to create a pulsating combustion stream (1A4). An ignitor mixture (1A6)is made available to the ignitor (410) via an ignitor input (412). Theignitor mixture (1A6) is a mixture of fuel and oxidant. FIG. 10 showsthe ignitor (410) extending into the mixing section (300) by passingthrough the first and second plates (103, 104). The ignitor (410) is influid communication with the combustion section (400) via a thirdignitor aperture (410A3) in the third plate (204). The first plate (103)has a first ignitor aperture (410A1), the second plate (104) has asecond ignitor aperture (410A2), and the third plate has a third ignitoraperture (410A3). In embodiments, the second plate (104) is in the formof a tubesheet (104A). In embodiments, the third plate (204) is in theform of a tubesheet (205).

Reference numerals (XI-XI) in FIG. 10 depict the oxidant sectionside-view that is elaborated upon in FIGS. 11 and 12.

FIG. 11

FIG. 11 shows one non-limiting embodiment of an oxidant inlet sectionside-view (XI-XI) that depicts a plurality of aerovalves (A, A′, A″,A′″, A^(N), A^(N+1)) inserted into a plurality of aerovalve apertures(106, 106A, 106B, 106C, 106D, 106 ^(N), 106 ^(N+1)) within the oxidantinlet section (100) tubesheet (104A), also showing an ignitor aperture(410A2, 410A21) positioned in the tubesheet (104A) for insertion of anignitor (410) through the tubesheet (104A) into the mixing section(300), and also showing a plurality of apertures (110A, 110B) in thetubesheet (104A) for introducing oxidant (1A1) into the mixing section(300).

FIG. 12

FIG. 12 elaborates upon the oxidant inlet section side-view (XI-XI)disclosure of FIG. 11 however showing the oxidant inlet section (100)tubesheet (104A) having 33 aerovalves (A, A′, A″, A′″, A^(N), A^(N+1))and 4 ignitor apertures (410A21, 410A22, 410A23, 410A24) that areconfigured to have a plurality of ignitors (410A, 410B, 410C, 410D)inserted into.

FIG. 13

FIG. 13 shows a zoomed-in view of a pulse combustion heat exchanger(1000) oxidant inlet section (100), fuel inlet section (200), mixingsection (300), combustion section (400), and a first portion of the heattransfer section (500) wherein one aerovalve (A) is positioned inbetween the oxidant inlet section (100) and the combustion section(400), and a third transition section (350) is positioned between themixing section (300) and the combustion section (400) and is providedwith a third coolant (351).

FIG. 13 shows a third transition plate (356) interposed in between thesecond plate (104) and third plate (204). The third transition section(350) is the interior in between the third transition plate (356) andthe second plate (204). The third transition section (350) is positionedbetween the mixing section (300) and the combustion section (400) and isprovided with a third coolant (351). In embodiments, the third coolant(351) is a cooling water supply (353). In embodiments, the thirdtransition plate (356) is in the form of a tubesheet (357). Inembodiments, the second plate (104) is in the form of a tubesheet(104A). In embodiments, the third plate (204) is in the form of atubesheet (205).

In embodiments, the third transition section (350) includes a pair ofparallel tubesheets (357, 205) defining a third interior space (350-1)therebetween. A third coolant inlet (352) is in fluid communication withthe third interior space (350-1). A third coolant outlet (354) is influid communication with the third interior space (350-1). The thirdcoolant inlet (352), the third interior space (350-1), and the thirdcoolant outlet (354) together define a third coolant path through thethird transition section (350).

FIG. 14

FIG. 14 elaborates upon the non-limiting embodiment of FIG. 13 and showsa first transition section (450) configured to cool in between thecombustion section (400) and the heat transfer section (500) via acoolant inlet (452) and a coolant outlet (454).

In embodiments, a first transition section (450) is positioned inbetween the combustion section (400) and the heat transfer section(500). In embodiments, the fourth plate (402) in between the combustionsection (400) and the heat transfer section (500) is in the form of atubesheet (403). In embodiments, another plate (456) in the form of atubesheet (457) with a plurality of apertures (458A, 458B, 458B. 458D,458E, 458 ^(N), 458 ^(N+1)) is spaced apart from and substantiallyparallel to the fourth plate (402) in between the combustion section(400) and the heat transfer section (500).

In embodiments, the first transition section (450) has a first pair ofparallel tubesheets (403, 457) defining a first interior space (450-1)therebetween. A first coolant inlet (452) is in fluid communication withthe first interior space (450-1) and first coolant outlet (454) is influid communication with the first interior space (450-1). The firstcoolant inlet (452), the first interior space (450-1), and the firstcoolant outlet (454) together define the first coolant path through thefirst transition section (450).

FIG. 15

FIG. 15 elaborates upon the non-limiting embodiment of FIGS. 10, 13, and14 and shows a plurality of aerovalves (A, A′) positioned in between theoxidant inlet section (100) and the combustion section (400), a firsttransition section (450) positioned between the combustion section (400)and the heat transfer section (500) that is provided with a firstcoolant (451), and a third transition section (350) is positionedbetween the mixing section (300) and the combustion section (400) and isprovided with a third coolant (351).

FIG. 16

FIG. 16 elaborates upon the non-limiting embodiment of FIG. 15 and showsthe fuel inlet section (200) contained within at least one fuel injector(370A, 370B), the fuel injector (370A, 370B) is comprised of a fuelinjector conduit (372A, 372B) connected to a fuel injector distributor(374A, 374B), the fuel injector conduit (372A, 372B) is configured toaccept fuel (1A2, 1A2A, 1A2B), and the fuel injector distributor (374A,374B) is configured to transfer the fuel (1A2, 1A2A, 1A2B) from the fuelinjector conduit (372A, 372B) into the mixing section (300).

FIG. 16 shows a plurality of aerovalves (A, A′) that are not equippedwith fuel inlet ports (1A, 1B, . . . ), fuel outlet ports (2A, 2B, . . .), or fuel transfer channels (3A, 3B, . . . ). Instead fuel (1A2) isintroduced into the mixing section (300) via a plurality of fuelinjectors (370A, 370B). The plurality of fuel injectors (370) mayinclude a first fuel injector (370A) and a second fuel injector (370B).

The first fuel injector (370A) is equipped with a first fuel injectorconduit (372A) and a first fuel injector distributor (374A) forintroducing a first fuel (1A2A) into the mixing section (300). The fuelinlet section (200) may be contained within the first fuel injectorconduit (372A). In embodiments, the first fuel injector distributor(374A) is equipped with one or a plurality of openings to permit uniformdistribution of the first fuel (1A2A) into the interior of the firstaerovalve (A).

The second fuel injector (370B) is equipped with a second fuel injectorconduit (372B) and a second fuel injector distributor (374B) forintroducing a second fuel (1A2B) into the mixing section (300). Inembodiments, the second fuel injector distributor (374B) is equippedwith one or a plurality of openings to permit uniform distribution ofthe second fuel (1A2B) into the interior of the second aerovalve (A′).The first fuel (1A2A) and second fuel (1A2B) may come from the samesource of fuel (1A2).

FIG. 16 shows the fuel inlet section (200) contained within theplurality of fuel injectors (370A, 370B). Each fuel injector (370A,370B) is comprised of a fuel injector conduit (372A, 372B) connected toa fuel injector distributor (374A, 374B), the fuel injector conduit(372A, 372B) is configured to accept fuel (1A2), and the fuel injectordistributor (374A, 374B) is configured to transfer the fuel (1A2) fromthe fuel injector conduit (372A, 372B) into the mixing section (300).

FIG. 17

FIG. 17 shows one non-limiting embodiment of a pulse combustion heatexchanger (1000) that is configured to accept oxidant (1A1) and fuel(1A2) and output a cooled combustion stream (1A5). The pulse combustionheat exchanger (1000) of FIG. 17 includes:

-   -   (a) an oxidant inlet section (100) that is configured to accept        oxidant (1A1);    -   (b) a fuel inlet section (200) that is configured to accept fuel        (1A2);    -   (c) a mixing section (300) including one aerovalve (A) that is        configured to accept and mix oxidant (1A1) from the oxidant        inlet section (100) with fuel (1A2) from the fuel inlet section        (200) to create an oxidant and fuel mixture (1A3);    -   (d) a combustion section (400) configured to receive and combust        the oxidant and fuel mixture (1A3) from the mixing section (300)        to produce a pulsating combustion stream (1A4);    -   (e) a heat transfer section (500) configured to receive the        combustion stream (1A4) from the combustion section (400), the        heat transfer section (500) including one or more resonance        conduits (502, 502A, 502B, 502C, 502D, 502E) that are configured        to transfer heat from the combustion stream (1A4) to an energy        sink (V108), wherein combustion of the oxidant and fuel mixture        (1A3) may continue to take place within the heat transfer        section (500);    -   (f) a first transition section (450) positioned between the        combustion section (400) and the heat transfer section (500),        the first transition section (450) comprising a first coolant        path configured to receive a first coolant (451);    -   (g) a second transition section (650) connected to the heat        transfer section (500) and configured to receive the combustion        stream (1A4) from the heat transfer section (500) and output a        cooled combustion stream (1A5), the second transition section        (650) comprising a second coolant path configured to receive a        second coolant (651);    -   (h) a decoupler section (600) connected to the second transition        section (650) and configured to accept the cooled combustion        stream (1A5) from the second transition section (650) and output        the cooled combustion stream (1A5) via a combustion stream        outlet (606); and    -   (i) a third transition section (350) positioned between the        mixing section (300) and the combustion section (400) that is        provided with a third coolant (351).

In embodiments, the first transition section (450) comprises: a firstpair of parallel tubesheets (403, 457) defining a first interior space(450-1) therebetween, a first coolant inlet (452) in fluid communicationwith the first interior space (450-1) that is configured to receive afirst coolant (651), and a first coolant outlet (454) in fluidcommunication with the first interior space (450-1); wherein the firstcoolant inlet (452), the first interior space (450-1) and the firstcoolant outlet (454) together define the first coolant path through thefirst transition section (450).

In embodiments, the second transition section (650) comprises: a secondpair of parallel tubesheets (603, 657) defining a second interior space(650-1) therebetween, a second coolant inlet (652) in fluidcommunication with the second interior space (650-1) that is configuredto receive a second coolant (651), and a second coolant outlet (654) influid communication with the second interior space (650-1), wherein thesecond coolant inlet (652), the second interior space (650-1) and thesecond coolant outlet (654) together define the second coolant paththrough the second transition section (450).

In embodiments, the second transition section (650) cools a portion ofthe combustion stream (1A4) that is evacuated from the heat transfersection (500) to form cooled combustion stream (1A5). In embodiments,both the heat transfer section (500) and the second transition section(650) cool a portion of the combustion stream (1A4) that is evacuatedfrom the heat transfer section (500) to form a cooled combustion stream(1A5). In embodiments, the combustion stream (1A4) that leaves thecombustion section (400) may be partially cooled in the heat transfersection (500) to form a cooled combustion stream (1A5). In embodiments,the combustion stream (1A4) that leaves the combustion section (400) maybe partially cooled in the second transition section (650) to form acooled combustion stream (1A5).

In embodiments, the second pair of parallel tubesheets (603, 657) aredefined by a fifth plate (602) and a sixth plate (656). The fifth plate(602) separates the heat transfer section (500) from the second interiorspace (650-1) of the second transition section (650). In embodiments,the fifth plate (602) is in the form of a tubesheet (603) having aplurality of apertures for inserting resonance conduits (502A, 502B,502C, 502D, 502E) into. In embodiments, the sixth plate (656) separatesthe second interior space (650-1) of the second transition section (650)from the decoupler section (600). In embodiments, the sixth plate (656)is in the form of a tubesheet (657) having a plurality of apertures forinserting resonance conduits (502A, 502B, 502C, 502D, 502E) into.

In embodiments, the third transition section (350) comprises: a thirdpair of parallel tubesheets (357, 205) defining a third interior space(350-1) therebetween, a third coolant inlet (352) in fluid communicationwith the third interior space (350-1), and a third coolant outlet (354),in fluid communication with the third interior space (350-1), whereinthe third coolant inlet (352), the third interior space (350-1) and thethird coolant outlet (354) together define a third coolant path throughthe third transition section (350).

In embodiments, the plurality of resonance conduits (502A, 502B, 502C,502D, 502E) define the heat transfer section (500). The heat transfersection (500) is connected to the decoupler section (600). The decouplersection (600) has an interior that is defined by the sixth plate (656)and a combustion stream outlet (606).

The oxidant (1A1) and fuel (1A2) mix within the mixing section (300)within the aerovalve (A) and form an oxidant and fuel mixture (1A3). Theoxidant and fuel mixture (1A3) is transferred from the mixing section(300) into the combustion section (400) where it is ignited to form apulsating combustion stream (1A4).

In embodiments, the resonance conduits (502, 502A, 502B, 502C, 502D,502E, 502 ^(N), 502 ^(N+1)) may have a radiation shield (504, 504A,504B, 504C) inserted within them to minimize heat loss and limit theheat transferred from the combustion section (400) to the tubesheets(403, 457) in between the combustion section (400) and the heat transfersection (500). In embodiments, the radiation shield (504, 504A, 504B,504C) may be a tube or pipe or conduit of a lesser diameter than theresonance conduits (502, 502A, 502B, 502C, 502D, 502E, 502 ^(N), 502^(N+1)) and inserted into each aperture (404, 404A, 404B, 404 ^(N), 404^(N+1)) in the tubesheet (403) inside of each resonance conduit (502).

In embodiments, the fourth plate (402) or tubesheet (403) closest to thecombustion section (400) may be connected to the fifth plate (602) ofthe tubesheet (603) closest to the decoupler section (600) via a firstsupport member (510) and a second support member (512).

The first support member (510) is connected to the fourth plate (402)via a first support member first connection (510X). The first supportmember (510) is connected to the fifth plate (602) first support membersecond connection (510Y). The second support member (512) is connectedto the fourth plate (402) via a second support member first connection(512X). The second support member (512) is connected to the fifth plate(602) second support member second connection (512Y).

In embodiments the resonance conduits (502, 502A, 502B, 502C, 502D,502E, 502 ^(N), 502 ^(N+1)) and the support members (510, 512) may passthrough a first baffle (506) and a second baffle (508).

FIG. 18

FIG. 18 elaborates upon the non-limiting embodiment of FIG. 17 howeverdepicts the mixing section (300) with a plurality of aerovalves (A, A′,A″).

FIG. 19

FIG. 19 depicts one non-limiting embodiment of a vessel (V100) equippedwith a first pulse combustion heat exchanger (1000A) and a second pulsecombustion heat exchanger (1000B), the first pulse combustion heatexchanger (1000A) has a first flange (PC1A) that is connected to a firstvessel flange (V1F) and a second flange (PC2A) that is connected to asecond vessel flange (V2F), and the second pulse combustion heatexchanger (1000B) has a first flange (PC1B) that is connected to a thirdvessel flange (V3F) and a second flange (PC2B) that is connected to afourth vessel flange (V4F).

FIG. 20

FIG. 20 depicts a pulse combustion heat exchanger (1000) having a firsttransition section (450) with a first coolant inlet (452) and a firstcoolant outlet (454), a second transition section (650) with a secondcoolant inlet (652) and a second coolant outlet (654), a thirdtransition section (350) with a third coolant inlet (352) and a thirdcoolant outlet (354), and a coolant recycling drum (800) in fluidcommunication with the first coolant inlet (452), the second coolantinlet (652), and the third coolant inlet (352) via a coolant transferconduit (817).

FIG. 20 shows one non-limiting embodiment of a pulse combustion heatexchanger (1000) including a coolant recycling drum (800). The coolantrecycling drum (800) is configured to accept a source of water (802) viaa water inlet (804). A level sensor (LT1) is configured to measure thelevel of water (802) within the coolant recycling drum (800) and permitwater (802) to enter via a water inlet (804) on level control through alevel control valve (LV1).

Steam (806) is generated within the first transition section (450),second transition section (650), and third transition section (350) ofthe pulse combustion heat exchanger (1000). The generated steam (806)from each section (450, 650, 350) is sent to the coolant recycling drum(800) via a steam conduit (821) and drum inlet (822). The coolantrecycling drum (800) is equipped with a pressure sensor (PT0). When apre-determined pressure within the coolant recycling drum (800) isachieved, steam (806) is released from the coolant recycling drum (800)via a steam outlet (808) on pressure control where it then passesthrough a pressure control valve (PV0).

FIG. 20 shows the first transition section (450) provided with a firstcoolant inlet (452) and a first coolant outlet (454), the secondtransition section (650) provided with a second coolant inlet (652) anda second coolant outlet (654), and the third transition section (350)having a third coolant inlet (352) and a third coolant outlet (354). Thethird transition section (350) is between the mixing section (300) andthe combustion section (400).

The pulse combustion heat exchanger (1000) further comprises a coolantrecycling drum (800) having a drum outlet (812) in fluid communicationwith the first, second, and third coolant inlets (452, 652, 352) andfurther having drum inlet (822) in fluid communication with the first,second, and third coolant outlets (454, 654, 354).

In embodiments, a first restriction orifice (RO1) is positioned betweenthe coolant recycling drum (800) and the first coolant inlet (452). Inembodiments, a second restriction orifice (RO2) is positioned in betweenthe coolant recycling drum (800) and the second coolant inlet (652). Inembodiments, a third restriction orifice (RO3) is positioned between thecoolant recycling drum (800) and the third coolant inlet (352).

FIG. 21

FIG. 21 elaborates upon the non-limiting embodiment of FIG. 20 includinga recycling pump (810) interposed on the coolant transfer conduit (817)to pressurize the coolant (818) provided by the coolant recycling drum(800) and provide supply coolant (815) to the first coolant inlet (452),the second coolant inlet (652), and the third coolant inlet (352).

FIG. 21 shows a recycling pump (810) interposed between the drum outlet(812) and the first, second, and third coolant inlets (452, 652, 352),the recycling pump (810) configured to supply coolant (815) underpressure to the first and second coolant inlets (452, 652). The firstcoolant inlet (452) is configured to receive a first coolant (451). Thesecond coolant inlet (652) is configured to receive a second coolant(651). The third coolant inlet (352) is configured to receive a thirdcoolant (351). The first, second, and third coolants (451, 651, 351) aretransferred to the first coolant inlet (452), the second coolant inlet(652), and the third coolant inlet (352) from the coolant recycling drum(800).

In embodiments, a first restriction orifice (RO1) is positioned betweenthe recycling pump (810) and the first coolant inlet (452). Inembodiments, a second restriction orifice (RO2) is positioned in betweenthe recycling pump (810) and the second coolant inlet (652). Inembodiments, a third restriction orifice (RO3) is positioned between thecoolant recycling drum (800) and the third coolant inlet (352). Inembodiments, a third transition section (350) in between the mixingsection (300) and the combustion section (400) has a third coolant inlet(352) and a third coolant outlet (354),

In embodiments, the coolant recycling drum (800) has a drum outlet (812)in fluid communication with the third coolant inlet (352) and furtherhaving drum inlet (822) in fluid communication with the third coolantoutlet (354). In embodiments, a recycling pump (810) is interposedbetween the drum outlet (812) and the third coolant inlet (352), therecycling pump (810) configured to supply coolant (815) under pressureto the third coolant inlets (352). In embodiments, a third restrictionorifice (RO3) is positioned between the coolant recycling drum (800) andthe third coolant inlet (352).

The pulse combustion heat exchanger (1000) such as that employed in thepresent disclosure, typically operates in the following manner. Oxidant(1A1) and fuel (1A2) are introduced to the mixing section (300) to forman oxidant and fuel mixture (1A3) which is then ignited. The oxidant andfuel mixture (1A3) may be ignited by an ignitor (410), a plurality ofignitors (410A, 410B), or by the combustion stream (1A4) within thecombustion section (400). The oxidant and fuel mixture (1A3) may beignited in the mixing section (300) or the combustion section (400).Explosion of the oxidant and fuel mixture (1A3) causes a sudden increasein volume and evolution of a combustion stream (1A4) which pressurizesthe combustion section (400). A sudden increase in volume, triggered bythe rapid increase in temperature and evolution of the combustion stream(1A4), pressurizes combustion section (400). As the hot combustionstream (1A4) expands, the aerovalve (A) acts as a fluidic diode andpermits preferential flow in the direction of resonance conduits (502,502A, 502B, 502C, 502D, 502E, 502 ^(N), 502 ^(N+1)). As the hot gas ofthe combustion stream (1A4) expands, preferential flow in the directionof the resonance conduits (502, 502A, 502B, 502C, 502D, 502E, 502 ^(N),502 ^(N+1)) of the heat transfer section (500) is achieved withsignificant momentum. A vacuum is then created in the combustion section(400) due to the inertia of the combustion stream (1A4) within theresonance conduits (502, 502A, 502B, 502C, 502D, 502E, 502 ^(N), 502^(N+1)). Only a small fraction of the combustion stream (1A4) is thenpermitted to return to the combustion section (400), with the balance ofthe combustion stream (1A4) exiting the heat transfer section (500).Because the pressure of the combustion section (400) is then belowatmospheric pressure, further oxidant and fuel mixture (1A3) is drawninto the combustion section (400) and ignition or auto-ignition takesplace. The aerovalve (A) thereafter constrains reverse flow, and thecycle begins anew. Once the first cycle is initiated, operation isthereafter self-sustaining or self-aspirating.

In the present disclosure, the aerodynamic valve, or aerovalve (A), hasno moving parts. In embodiments, after the oxidant and fuel mixture(1A3) has ignited in the combustion section (400), a boundary-layerbuilds in the aerovalve (A) and turbulent eddies choke off much of thereverse flow. Moreover, the combustion stream (1A4) formed in thecombustion section (400) is of a much higher temperature than the inputoxidant (1A1), fuel (1A2), and oxidant and fuel mixture (1A3).Accordingly, the viscosity of the combustion stream (1A4) is much higherand the reverse resistance of the inner first diameter (D1) of theaerovalve (A), in turn, is much higher than that for forward flowthrough the same opening. Such phenomena, along with the high inertia ofcombustion stream (1A4) passing through the resonance conduits (502,502A, 502B, 502C, 502D, 502E, 502 ^(N), 502 ^(N+1)), combine to yieldpreferential and mean flow from oxidant inlet section (100) and fuelinlet section (200) to the mixing section (300), combustion section(400), heat transfer section (500), and decoupler section (600).

Thus, the preferred pulse combustion heat exchanger (1000) is aself-aspirating engine, drawing its own oxidant and fuel into thecombustion section (400) followed by auto-ignition. In embodiments, thepulse combustion heat exchanger (1000) is not self-igniting but insteadrelies upon an ignitor (410) or a plurality of ignitors (410A, 410B,410C) positioned within the combustion section (400) to cause theoxidant and fuel mixture (1A3) to ignite. In embodiments, the pulsecombustion heat exchanger (1000) is self-igniting. The disclosed pulsecombustion heat exchanger (1000) regulates its own stoichiometry withinranges of firing without the need for extensive controls to regulate thefuel feed to oxidant mass flow rate ratio. As the fuel feed rate isincreased, the strength of the pressure pulsations in the combustionsection (400) increases, which in turn increases the amount of oxidant(1A1) aspirated by the aerovalve (A), thus allowing the pulse combustionheat exchanger (1000) to automatically maintain a substantially constantstoichiometry over its designed firing range. The induced stoichiometrycan be changed by modifying the aerovalve (A) fluidic diodicity.

The preferred pulse combustion heat exchanger (1000) used herein forfiring is based on a Helmholtz configuration with an aerovalve (A). Thepressure fluctuations, which are combustion-induced in the Helmholtzresonator combustion section (400), coupled with the fluidic diodicityof the aerovalve (A), causes a bias flow of oxidant (1A1), fuel (1A2),oxidant and fuel mixture (1A3), and combustion stream (1A4) from thecombustion section (400) to the resonance conduits (502, 502A, 502B,502C, 502D, 502E, 502 ^(N), 502 ^(N+1)) of the heat transfer section(500). This results in the oxidant (1A1) being self-aspirated by thecombustion section (400) and for an average pressure boost to develop inthe combustion section (400) to expel a combustion stream (1A4) throughthe resonance conduits (502, 502A, 502B, 502C, 502D, 502E, 502 ^(N), 502^(N+1)).

In embodiments, the combustion stream (1A4) temperature is in a range offrom about 1400° to about 3000° F. In the vessel (V100), acousticpressure wave level in a range of from about 140 to about 195 dB areachievable. In the vessel (V100), temperatures of the material (V106)may range of from about 1000° to about 1700° F. In embodiments, thematerial (V106) may be a solid, liquid, vapor, or gas. The solidmaterial (V106) may include particles. The production of an intenseacoustic wave is an inherent characteristic of pulse combustion. Soundintensity adjacent to the wall of the pulsating combustion section (400)is often in the range of 140-195 dB, and may be altered depending on thedesired acoustic field frequency to accommodate the specific applicationundertaken by the pulse combustion heat exchanger (1000).

In embodiments, the pulse combustion heat exchanger (1000) according tothe present disclosure generates a pulsating flow of combustion productsand an acoustic pressure wave. In embodiments, the pulse combustion heatexchanger (1000) of the present disclosure produces pressureoscillations or fluctuations in the range of from about 1 psi to about40 psi and particularly between about 1 psi and 25 psi peak to peak.These fluctuations are substantially sinusoidal. These pressurefluctuation levels are on the order of a sound pressure range of fromabout 140 dB to about 195 dB and particularly between about 161 dB and190 dB. The acoustic field frequency range depends primarily on thecombustor design and is only limited by the fuel flammabilitycharacteristics. In embodiments, the combustion section (400) operatesat a frequency in a range of from about 45 Hz to about 200 Hz

A rapid pressure oscillation through the combustion section (400)generates an intense oscillating or fluctuating flow field. Theoscillating or fluctuating flow field causes the combustion stream (1A4)to be swept away from the oxidant and fuel mixture (1A3), which isfiring within the combustion section (400), thus providing access tooxidant (1A1) or fuel (1A2) with little or no diffusion limitation.Secondly, the pulse combustion heat exchanger (1000) experiences veryhigh mass and heat transfer rates within the combustion section (400)and heat transfer section (500).

In embodiments, the combustion section (400) and resonance conduits(502, 502A, 502B, 502C, 502D, 502E, 502 ^(N), 502 ^(N+1)) of the heattransfer section (500) form a tuned Helmholtz resonator. The aerovalve(A) acts as a diode such that self-oxidant aspiration is affected inresponse to an oscillating pressure in the combustion section (400)induced as a result of heat and mass release from combustion therein.

Various other modifications can be made to the pulse combustion heatexchanger (1000) of the present disclosure. For example, if desired,resonance conduits (502, 502A, 502B, 502C, 502D, 502E, 502 ^(N), 502^(N+1)) may employ a number of different designs. For example, theresonance conduits (502, 502A, 502B, 502C, 502D, 502E, 502 ^(N), 502^(N+1)) may flare continuously outwardly allowing the entire resonancetube to act as a diffuser to reduce gas exit velocity from thecombustion section (400). Moreover, resonance conduits (502, 502A, 502B,502C, 502D, 502E, 502 ^(N), 502 ^(N+1)) may be essentially straight, buthave at its outer end a diffuser section that consists of an outwardlyflaring tailpipe section, or alternatively, may integrate a diffusersection at the end nearest combustion section (400) with an essentiallystraight tube extending therefrom.

FIG. 22

FIG. 22 discloses a method to form a cooled combustion stream, themethod includes:

-   -   (a) providing a pulse combustion heat exchanger having a        longitudinal axis that includes:        -   (a1) an oxidant inlet section connected to a mixing section,            the oxidant inlet section configured to accept oxidant;        -   (a2) a fuel inlet section connected to the mixing section,            the fuel inlet section configured to accept fuel;        -   (a3) a mixing section connected to a combustion section, the            mixing section is configured to accept oxidant from the            oxidant inlet section and fuel from the fuel inlet section            and mix the oxidant with the fuel to form an oxidant and            fuel mixture;        -   (a4) a combustion section connected to a heat transfer            section, the combustion section configured to accept and            combust the oxidant and fuel mixture from the mixing section            to form a pulsating combustion stream;        -   (a5) a heat transfer section connected to a decoupler            section, the heat transfer section is configured to accept            the pulsating combustion stream from the combustion section            and cool the combustion stream by transferring heat to a            heat transfer material;        -   (a6) a decoupler section configured to acoustically            disengage the cooled combustion stream from the heat            transfer section;    -   (b) introducing oxidant to the oxidant inlet section;    -   (c) introducing fuel to the fuel inlet section;    -   (d) introducing oxidant from the oxidant inlet section to the        mixing section;    -   (e) introducing fuel from the fuel inlet section to the mixing        section;    -   (f) mixing the oxidant of step (d) with the fuel of step (e) to        form an oxidant and fuel mixture;    -   (g) introducing the oxidant and fuel mixture of step (f) into        the combustion section;    -   (h) igniting the oxidant and fuel mixture after step (g) to form        a pulsating combustion stream;    -   (i) introducing the pulsating combustion stream of step (h) into        the heat transfer section;    -   (j) transferring heat from the pulsating combustion stream after        step (i) to a heat transfer medium while cooling a portion of        the pulsating combustion stream to form a cooled combustion        stream; and    -   (k) transferring the cooled combustion stream of step (j) to the        decoupler section and acoustically disengaging the cooled        combustion stream from the heat transfer section.

In embodiments, the method further includes: (a) providing a first metalsurface in between the combustion section and heat transfer section; and(b) contacting the first metal surface with a first coolant to cool thefirst metal surface. In embodiments, the first transition section (450)is the first metal surface. In embodiments, the first coolant is waterand heat is removed from the first metal surface to generate a firststeam.

In embodiments, the method further includes: (a) providing a coolantrecycling drum having coolant contained therein and having a drum outletin fluid communication with the first metal surface and further havingdrum inlet configured to accept the first steam; (b) transferringcoolant from the coolant recycling drum to contact the first metalsurface; (c) generating a first steam; and (d) transferring the firststeam to the drum inlet of the coolant recycling drum.

In embodiments, the method further includes: (a) providing a firstrestriction orifice positioned between the drum outlet and the firstmetal surface; (b) prior to contacting the first metal surface with thecoolant, reducing the pressure of the coolant by passing the coolantthrough the first restriction orifice.

In embodiments, the method further includes: (a) providing a recyclingpump in between the drum outlet and the first metal surface, therecycling pump is configured to supply coolant under pressure to thefirst metal surface; (b) pressurizing the coolant; and (c) passing thepressurized coolant through the first restriction orifice.

In embodiments, the method further includes: (a) providing a secondmetal surface in between the heat transfer section and decouplersection; (b) contacting the second metal surface with a second coolantto cool the second metal surface. In embodiments, the second transitionsection (650) is the second metal surface. In embodiments, the secondcoolant is water and heat is removed from the second metal surface togenerate a second steam.

In embodiments, the method further includes: (a) providing a coolantrecycling drum having coolant contained therein and having a drum outletin fluid communication with the second metal surface and further havingdrum inlet configured to accept the second steam; (b) transferringcoolant from the coolant recycling drum to contact the second metalsurface; (c) generating a second steam; and (d) transferring the secondsteam to the drum inlet of the coolant recycling drum.

In embodiments, the method further includes: (a) providing a secondrestriction orifice positioned between the drum outlet and the secondmetal surface; (b) prior to contacting the second metal surface with thecoolant, reducing the pressure of the coolant by passing the coolantthrough the second restriction orifice.

In embodiments, the method further includes: (a) providing a recyclingpump in between the drum outlet and the second metal surface, therecycling pump is configured to supply coolant under pressure to thesecond metal surface; (b) pressurizing the coolant; and (c) passing thepressurized coolant through the second restriction orifice.

In embodiments, the method further includes: (a) providing a third metalsurface in between the mixing section and combustion section; (b)contacting the third metal surface with a third coolant to cool thethird metal surface. In embodiments, the third transition section (350)is the third metal surface. In embodiments, the third coolant is waterand heat is removed from the third metal surface to generate a thirdsteam.

In embodiments, the method further includes: (a) providing a coolantrecycling drum having coolant contained therein and having a drum outletin fluid communication with the third metal surface and further havingdrum inlet configured to accept the third steam; (b) transferringcoolant from the coolant recycling drum to contact the third metalsurface; (c) generating a third steam; and (d) transferring the thirdsteam to the drum inlet of the coolant recycling drum.

In embodiments, the method further includes: (a) providing a thirdrestriction orifice positioned between the drum outlet and the thirdmetal surface; (b) prior to contacting the third metal surface with thecoolant, reducing the pressure of the coolant by passing the coolantthrough the third restriction orifice.

In embodiments, the method further includes: (a) providing a recyclingpump in between the drum outlet and the third metal surface, therecycling pump is configured to supply coolant under pressure to thethird metal surface; (b) pressurizing the coolant; and (c) passing thepressurized coolant through the third restriction orifice.

In embodiments, the method further includes: (a) providing a pluralityof aerovalves within the mixing section, the aerovalves have aconverging-diverging geometry and are configured to provide turbulentmixing of the oxidant and fuel within the mixing section and minimizebackflow of the oxidant and fuel mixture from the mixing section intothe oxidant inlet section or fuel inlet section; (b) subjecting theoxidant to a first drop in pressure from the oxidant inlet section tothe mixing section; and (c) subjecting the fuel to a second drop inpressure from the fuel inlet section to the mixing section.

In embodiments, the method further includes: (a) providing plurality ofignitors in fluid communication with the combustion section, eachignitor having an ignitor input configured to introduce an ignitormixture to the ignitor, the ignitor input being in fluid communicationwith an ignitor oxidant supply and an ignitor fuel supply; (b)introducing an ignitor mixture to each of the plurality of ignitors; (c)igniting the oxidant and fuel mixture within the combustion section withthe plurality of ignitors.

It will be appreciated that the foregoing examples, given for purposesof illustration, are not to be construed as limiting the scope of thisdisclosure. Although only a few exemplary embodiments of this disclosurehave been described in detail above, those skilled in the art willreadily appreciate that many variation of the theme are possible in theexemplary embodiments without materially departing from the novelteachings and advantages of this disclosure. Accordingly, all suchmodifications are intended to be included within the scope of thisdisclosure that is defined in the following claims and all equivalentsthereto. Further, it is recognized that many embodiments may beconceived in the design of a given system that do not achieve all of theadvantages of some embodiments, yet the absence of a particularadvantage shall not be construed to necessarily mean that such anembodiment is outside the scope of the present disclosure.

Thus, specific systems and methods of an automated fluidized bed leveland density measurement system have been disclosed. It should beapparent, however, to those skilled in the art that many moremodifications besides those already described are possible withoutdeparting from the inventive concepts herein. The inventive subjectmatter, therefore, is not to be restricted except in the spirit of thedisclosure. Moreover, in interpreting the disclosure, all terms shouldbe interpreted in the broadest possible manner consistent with thecontext. In particular, the terms “comprises” and “comprising” should beinterpreted as referring to elements, components, or steps in anon-exclusive manner, indicating that the referenced elements,components, or steps may be present, or utilized, or combined with otherelements, components, or steps that are not expressly referenced.

Although the foregoing text sets forth a detailed description ofnumerous different embodiments of the disclosure, it should beunderstood that the scope of the disclosure is defined by the words ofthe claims set forth at the end of this patent. The detailed descriptionis to be construed as exemplary only and does not describe everypossible embodiment of the disclosure because describing every possibleembodiment would be impractical, if not impossible. Numerous alternativeembodiments could be implemented, using either current technology ortechnology developed after the filing date of this patent, which wouldstill fall within the scope of the claims defining the disclosure.

Thus, many modifications and variations may be made in the techniquesand structures described and illustrated herein without departing fromthe spirit and scope of the present disclosure. Accordingly, it shouldbe understood that the methods and apparatus described herein areillustrative only and are not limiting upon the scope of the disclosure.

Unless the context dictates the contrary, all ranges set forth hereinshould be interpreted as being inclusive of their endpoints, andopen-ended ranges should be interpreted to include commerciallypractical values. Similarly, all lists of values should be considered asinclusive of intermediate values unless the context indicates thecontrary.

The recitation of ranges of values herein is merely intended to serve asa shorthand method of referring individually to each separate valuefalling within the range. Unless otherwise indicated herein, eachindividual value is incorporated into the specification as if it wereindividually recited herein. All methods described herein can beperformed in any suitable order unless otherwise indicated herein orotherwise clearly contradicted by context. The use of any and allexamples, or exemplary language (e.g., “such as”) provided with respectto certain embodiments herein is intended merely to better illuminatethe disclosure and does not pose a limitation on the scope of thedisclosure otherwise claimed. No language in the specification should beconstrued as indicating any non-claimed element essential to thepractice of the disclosure.

Groupings of alternative elements or embodiments of the disclosuredisclosed herein are not to be construed as limitations. Each groupmember can be referred to and claimed individually or in any combinationwith other members of the group or other elements found herein. One ormore members of a group can be included in, or deleted from, a group forreasons of convenience and/or patentability. When any such inclusion ordeletion occurs, the specification is herein deemed to contain the groupas modified thus fulfilling the written description of all Markushgroups used in the appended claims.

It should be apparent to those skilled in the art that many moremodifications besides those already described are possible withoutdeparting from the inventive concepts herein. The inventive subjectmatter, therefore, is not to be restricted except in the spirit of theappended claims. Moreover, in interpreting both the specification andthe claims, all terms should be interpreted in the broadest possiblemanner consistent with the context. In particular, the terms “comprises”and “comprising” should be interpreted as referring to elements,components, or steps in a non-exclusive manner, indicating that thereferenced elements, components, or steps may be present, or utilized,or combined with other elements, components, or steps that are notexpressly referenced. Where the specification claims refers to at leastone of something selected from the group consisting of A, B, C . . . andN, the text should be interpreted as requiring only one element from thegroup, not A plus N, or B plus N, etc.

Unless defined otherwise, all technical and scientific terms used hereinhave the same meaning as commonly understood by one of ordinary skill inthe art to which this invention belongs. Although any methods andmaterials similar or equivalent to those described herein can also beused in the practice or testing of the present invention, a limitednumber of the exemplary methods and materials are described herein.

It must be noted that as used herein and in the appended claims, thesingular forms “a”, “an”, and “the” include plural referents unless thecontext clearly dictates otherwise.

LISTING OF REFERENCE NUMERALS

-   aerovalve (A, A′, A″, A′″, A″, A^(N), A^(N+1))-   oxidant inlet (1A0)-   oxidant and fuel mixture outlet (2A0)-   rear end (1E1)-   forward end (2E1)-   oxidant (1A1)-   fuel (1A2)-   first fuel (1A2A)-   second fuel (1A2B)-   oxidant and fuel mixture (1A3)-   combustion stream (1A4)-   cooled combustion stream (1A5)-   ignitor mixture (1A6)-   first ignitor mixture (1A6A)-   second ignitor mixture (1A6B)-   exchanger longitudinal axis (X2)-   aerovalve longitudinal axis (X1)-   rearwardly facing rear surface (1E1S)-   forwardly facing forward surface (2E1S)-   interior (A-IN)-   outer surface (S)-   first inner conical surface (S1)-   second inner conical surface (S2)-   third inner conical surface (S3)-   first angle (A1)-   second angle (A2)-   third angle (A3)-   outer diameter (D0)-   first inner diameter (D1)-   second inner diameter (D2)-   third inner diameter (D3)-   first cross-sectional side view (I-I)-   second cross-sectional side view (III-III)-   third cross-sectional side view (V-V)-   first forward view (II-II)-   second forward view (IV-IV)-   third forward view (VI-VI)-   first fuel inlet port (1A)-   second fuel inlet port (1B)-   third fuel inlet port (1C)-   fourth fuel inlet port (1D)-   fifth fuel inlet port (1E)-   sixth fuel inlet port (1F)-   seventh fuel inlet port (1G)-   eighth fuel inlet port (1H)-   ninth fuel inlet port (1 i)-   tenth fuel inlet port (1J)-   eleventh fuel inlet port (1K)-   twelfth fuel inlet port (1L)-   first fuel outlet port (2A)-   second fuel outlet port (2B)-   third fuel outlet port (2C)-   fourth fuel outlet port (2D)-   fifth fuel outlet port (2E)-   sixth fuel outlet port (2F)-   seventh fuel outlet port (2G)-   eighth fuel outlet port (2H)-   ninth fuel outlet port (2 i)-   tenth fuel outlet port (2J)-   eleventh fuel outlet port (2K)-   twelfth fuel outlet port (2L)-   first fuel transfer channel (3A)-   second fuel transfer channel (3B)-   third fuel transfer channel (3C)-   fourth fuel transfer channel (3D)-   fifth fuel transfer channel (3E)-   sixth fuel transfer channel (3F)-   seventh fuel transfer channel (3G)-   eighth fuel transfer channel (3H)-   ninth fuel transfer channel (3I)-   tenth fuel transfer channel (3J)-   eleventh fuel transfer channel (3K)-   twelfth fuel transfer channel (3L)-   channel diameter (XX1)-   total length (L)-   first length (L1)-   second length (L2)-   third length (L3)-   fourth length (L4)-   fifth length (L5)-   sixth length (L6)-   seventh length (L7)-   pulse combustion heat exchanger (1000)-   first pulse combustion heat exchanger (1000A)-   second pulse combustion heat exchanger (1000B)-   first flange (PC1, PC1A, PC1B)-   second flange (PC2, PC2A, PC2B)-   vessel (V100)-   interior (V102)-   side wall (V104)-   heat transfer medium (V106)-   energy sink (V108)-   inlet (V110)-   mass input (V111)-   outlet (V112)-   mass output (V113)-   first vessel flange (V1F)-   second vessel flange (V2F)-   third vessel flange (V3F)-   fourth vessel flange (V4F)-   oxidant inlet section (100)-   oxidant inlet (102)-   first plate (103)-   second plate (104)-   tubesheet (104A)-   aerovalve aperture (106, 106A, 106B, 106C, 106D, 106 ^(N), 106    ^(N+1))-   first fuel aperture (108)-   first first fuel aperture (108A)-   second first fuel aperture (108B)-   second fuel aperture (110)-   first second fuel aperture (110A)-   second second fuel aperture (110B)-   oxidant inlet section side-view (XI-XI)-   fuel inlet section (200)-   fuel inlet (202)-   first fuel inlet (202A)-   second fuel inlet (202B)-   third plate (204)-   tubesheet (205)-   aperture (206, 206A, 206B, 206C, 206D, 206 ^(N), 206 ^(N+1))-   mixing section (300)-   third transition section (350)-   third interior space (350-1)-   third coolant (351)-   third coolant inlet (352)-   cooling water supply (353)-   third coolant outlet (354)-   cooling water return (355)-   third transition plate (356)-   tubesheet (357)-   inlet aperture (358)-   outlet aperture (359)-   aerovalve aperture (360, 360A, 360B)-   fuel injector (370)-   first fuel injector (370A)-   second fuel injector (370B)-   first fuel injector conduit (372A)-   second fuel injector conduit (372B)-   first fuel injector distributor (374A)-   second fuel injector distributor (374B)-   combustion section (400)-   fourth plate (402)-   tubesheet (403)-   aperture (404, 404A, 404B, 404C, 404D, 404 ^(N), 404 ^(N+1))-   first aperture (404A)-   second aperture (404B)-   third aperture (404C)-   fourth aperture (404D)-   fifth aperture (404E)-   first refractory section (406)-   second refractory section (408)-   combustion section side-view (IX-IX)-   ignitor (410)-   first ignitor (410A)-   second ignitor (410B)-   first ignitor aperture (410A1)-   second ignitor aperture (410A2)-   third ignitor aperture (410A3)-   first second ignitor aperture (410A21)-   second second ignitor aperture (410A22)-   third second ignitor aperture (410A23)-   fourth second ignitor aperture (410A24)-   ignitor input (412)-   first ignitor input (412A)-   second ignitor input (412B)-   first transition section (450)-   first interior space (450-1)-   first coolant (451)-   first coolant inlet (452)-   first coolant outlet (454)-   plate (456)-   tubesheet (457)-   aperture (458, 458A, 458B, 458C)-   heat transfer section (500)-   resonance conduit (502, 502A, 502B, 502C, 502D, 502E, 502 ^(N), 502    ^(N+1))-   first resonance conduit (502A)-   second resonance conduit (502B)-   third resonance conduit (502C)-   fourth resonance conduit (502D)-   fifth resonance conduit (502E)-   radiation shield (504, 504A, 504B, 504C)-   first baffle (506)-   second baffle (508)-   first support member (510)-   second support member (512)-   first support member first connection (510X)-   first support member second connection (510Y)-   second support member first connection (512X)-   second support member second connection (512Y)-   decoupler section (600)-   fifth plate (602)-   tubesheet (603)-   aperture (604, 604A, 604B, 604C, 604D, 604 ^(N), 604 ^(N+1))-   combustion stream outlet (606)-   second transition section (650)-   second interior space (650-1)-   second coolant (651)-   second coolant inlet (652)-   second coolant outlet (654)-   sixth plate (656)-   tubesheet (657)-   aperture (658, 658A, 658B, 658C)-   coolant recycling drum (800)-   water (802)-   water inlet (804)-   level sensor (LT1)-   level control valve (LV1)-   steam (806)-   steam outlet (808)-   pressure sensor (PT0)-   pressure control valve (PV0)-   third transition section coolant (809)-   recycling pump (810)-   pump suction conduit (811)-   drum outlet (812)-   pump discharge conduit (813)-   first transition section coolant (814)-   supply coolant (815)-   second transition section coolant (816)-   coolant transfer conduit (817)-   coolant (818)-   coolant (820)-   steam conduit (821)-   drum inlet (822)-   first temperature sensor (T1)-   second temperature sensor (T2)-   first restriction orifice (RO1)-   second restriction orifice (RO2)-   third restriction orifice (RO3)

What is claimed is:
 1. An aerovalve (A), having an aerovalvelongitudinal axis (X1), an outer surface (S) with an outer diameter(D0), an interior (A-IN), a rear end (1E1) having a rearwardly facingrear surface (1E1S), a forward end (2E1) having a forwardly facingforward surface (2E1S), and a total aerovalve length (L) defined betweenthe rear and forward ends (1E1, 2E1) along the aerovalve longitudinalaxis (X1), the aerovalve (A) further comprising: an oxidant inlet (1A0)located at the rear end (1E1), the oxidant inlet (1A0) configured tointroduce oxidant (1A1) into the interior (A-IN) of the aerovalve (A);an oxidant and fuel mixture outlet (2A0) located at the forward end(2E1), the oxidant and fuel mixture outlet (2A0) configured to expel anoxidant and fuel mixture (1A3) present in the interior (A-IN) of theaerovalve (A); a first plurality of fuel inlet ports (1A, 1B, 1C, . . .) opening to the outer surface (S), a second plurality of fuel outletports (2A, 2B, 2C, . . . ) opening to the interior (A-IN), and a thirdplurality of fuel transfer channels (3A, 3B, 3C, . . . ) configured totransfer fuel (1A2) from the first plurality of fuel inlet ports (1A,1B, 1C, . . . ) to the second plurality of fuel outlet ports (2A, 2B,2C, . . . ); a first inner conical surface (S1) tapering radiallyinwardly at a first angle (A1) to a first inner diameter (D1), the firstinner conical surface (S1) extending in the forward direction fromproximate the rear end (1E1) for a first length (L1) along the aerovalvelongitudinal axis (X1); a second inner conical surface (S2) expandingradially outwardly at a second angle (A2) to a second inner diameter(D2), the second inner conical surface (S2) extending in the forwarddirection from proximate the first inner conical surface (S1) for asecond length (L2) along the aerovalve longitudinal axis (X1), thesecond inner diameter (D2) being less than the outer diameter (D0); anda third inner conical surface (S3) expanding radially outwardly at athird angle (A3) to a third inner diameter (D3), the third inner conicalsurface (S3) extending in the forward direction from proximate thesecond inner conical surface (S2) for a third length (L3) along theaerovalve longitudinal axis (X1), the third inner diameter (D3) beinggreater than the first and second inner diameters (D1, D2) and less thanthe outer diameter (D0); wherein: the first angle (A1) is greater thanthe second angle (A2); the third angle (A3) is greater than the secondangle (A2); and the second plurality of fuel outlet ports (2A, 2B, 2C, .. . ) are positioned on the third inner conical surface (S3).
 2. Acylindrical aerovalve (A) according to claim 1, wherein the first angle(A1) ranges from between 30 degrees to 60 degrees.
 3. A cylindricalaerovalve (A) according to claim 1, wherein the second angle (A2) rangesfrom between 1.5 degrees to 11.25 degrees.
 4. The cylindrical aerovalve(A) according to claim 1, wherein the third angle (A3) ranges frombetween 11.25 degrees to 90 degrees.
 5. The cylindrical aerovalve (A)according to claim 1, wherein the total aerovalve length (L) to firstinner diameter (D1) ratio ranges from 2.5 to
 10. 6. The cylindricalaerovalve (A) according to claim 1, wherein the total aerovalve length(L) to outer diameter (D0) ratio ranges from 1 to
 8. 7. The cylindricalaerovalve (A) according to claim 1, wherein the first inner diameter(D1) to outer diameter (D0) ratio ranges from 1.25 to 3.75.
 8. A pulsecombustion heat exchanger (1000) that is configured to accept oxidant(1A1) and fuel (1A2) and output a cooled combustion stream (1A5),including: (a) an oxidant inlet section (100) that is configured toaccept oxidant (1A1); (b) a fuel inlet section (200) that is configuredto accept fuel (1A2); (c) a mixing section (300) including one or moreaerovalves in accordance with claim 1 (A, A′, A″); that are configuredto accept and mix oxidant (1A1) from the oxidant inlet section (100)with fuel (1A2) from the fuel inlet section (200) to create an oxidantand fuel mixture (1A3); (d) a combustion section (400) configured toreceive and combust the oxidant and fuel mixture (1A3) from the mixingsection (300) to produce a pulsating combustion stream (1A4); (e) a heattransfer section (500) configured to receive the combustion stream (1A4)from the combustion section (400), the heat transfer section (500)including one or more resonance conduits (502, 502A, 502B, 502C, 502D,502E) that are configured to transfer heat from the combustion stream(1A4) to an energy sink (V108), wherein combustion of the oxidant andfuel mixture (1A3) may continue to take place within the heat transfersection (500); (f) a first transition section (450) positioned betweenthe combustion section (400) and the heat transfer section (500), thefirst transition section (450) comprising a first coolant pathconfigured to receive a first coolant (451); (g) a second transitionsection (650) connected to the heat transfer section (500) andconfigured to receive the combustion stream (1A4) from the heat transfersection (500) and output a cooled combustion stream (1A5), the secondtransition section (650) comprising a second coolant path configured toreceive a second coolant (651); and (h) a decoupler section (600)connected to the second transition section (650) and configured toaccept the cooled combustion stream (1A5) from the second transitionsection (650) and output the cooled combustion stream (1A5) via acombustion stream outlet (606).
 9. The pulse combustion heat exchanger(1000) according to claim 8, wherein the first transition section (450)comprises: a first pair of parallel tubesheets (403, 457) defining afirst interior space (450-1) therebetween; a first coolant inlet (452)in fluid communication with the first interior space (450-1) andconfigured to receive the first coolant (451); and a first coolantoutlet (454) in fluid communication with the first interior space(450-1); wherein: the first coolant inlet (452), the first interiorspace (450-1) and the first coolant outlet (454) together define thefirst coolant path through the first transition section (450).
 10. Thepulse combustion heat exchanger (1000) according to claim 9, wherein thesecond transition section (650) comprises: a second pair of paralleltubesheets (603, 657) defining a second interior space (650-1)therebetween; a second coolant inlet (652) in fluid communication withthe second interior space (650-1) that is configured to receive thesecond coolant (652); and a second coolant outlet (654) in fluidcommunication with the second interior space (650-1); wherein: thesecond coolant inlet (652), the second interior space (650-1) and thesecond coolant outlet (654) together define the second coolant paththrough the second transition section (450).
 11. The pulse combustionheat exchanger (1000) according to claim 8, further comprising: a thirdtransition section (350) positioned between the mixing section (300) andthe combustion section (400) that is provided with a third coolant(351).
 12. The pulse combustion heat exchanger (1000) according to claim11, wherein the third transition section (350) comprises: a third pairof parallel tubesheets (357, 205) defining a third interior space(350-1) therebetween; a third coolant inlet (352) in fluid communicationwith the third interior space (350-1) that is configured to receive thethird coolant (351); and a third coolant outlet (354), in fluidcommunication with the third interior space (350-1); wherein: the thirdcoolant inlet (352), the third interior space (350-1) and the thirdcoolant outlet (354) together define a third coolant path through thethird transition section (350).
 13. The pulse combustion heat exchanger(1000) according to claim 8, further comprising: at least one ignitor(410, 410A, 410B) is in fluid communication with the combustion section(400); and an ignitor input (412) configured to introduce an ignitormixture (1A6) to the ignitor (410), the ignitor input (412) being influid communication with an ignitor oxidant supply and an ignitor fuelsupply.
 14. The pulse combustion heat exchanger (1000) according toclaim 13, further comprising: a plurality of ignitors (410A, 410B) influid communication with the combustion section (400).
 15. The pulsecombustion heat exchanger (1000) according to claim 8, furthercomprising: a vessel (V100) having an interior (V102) defined by atleast one side wall (V104); and a heat transfer medium (V106) occupyingthe vessel's interior (V102) and configured to accept heat from the heattransfer section (500) and serve as an energy sink (V108).
 16. The pulsecombustion heat exchanger (1000) according to claim 8, wherein: thefirst transition section (450) is provided with a first coolant inlet(452) and a first coolant outlet (454); the second transition section(650) is provided with a second coolant inlet (652) and a second coolantoutlet (654); the heat exchanger further comprises a coolant recyclingdrum (800) having a drum outlet (812) in fluid communication with thefirst and second coolant inlets (452, 652) and further having drum inlet(822) in fluid communication with the first and second coolant outlets(454, 654); and a recycling pump (810) is interposed between the drumoutlet (812) and the first and second coolant inlets (452, 652), therecycling pump (810) configured to supply coolant (815) under pressureto the first and second coolant inlets (452, 652).
 17. The pulsecombustion heat exchanger (1000) according to claim 16, furthercomprising: a first restriction orifice (RO1) positioned between therecycling pump (810) and the first coolant inlet (452); and a secondrestriction orifice (RO2) positioned in between the recycling pump (810)and the second coolant inlet (652).
 18. The pulse combustion heatexchanger (1000) according to claim 16, further comprising: a thirdtransition section (350) between the mixing section (300) and thecombustion section (400), the third transition section (350) having athird coolant inlet (352) and a third coolant outlet (354); wherein: thedrum outlet (812) is in fluid communication with the third coolant inlet(352) and the drum inlet (822) is in fluid communication with the thirdcoolant outlet (354); and the recycling pump (810) is interposed betweenthe drum outlet (812) and the third coolant inlet (352), the recyclingpump (810) configured to supply coolant (815) under pressure to thethird coolant inlet (352).
 19. The pulse combustion heat exchanger(1000) according to claim 18, further comprising: a first restrictionorifice (RO1) positioned between the recycling pump (810) and the firstcoolant inlet (452); a second restriction orifice (RO2) positioned inbetween the recycling pump (810) and the second coolant inlet (652); anda third restriction orifice (RO3) positioned between the coolantrecycling drum (800) and the third coolant inlet (352).
 20. The pulsecombustion heat exchanger (1000) according to claim 8, furthercomprising: a third transition section (350) between the mixing section(300) and the combustion section (400), the third transition section(350) having a third coolant inlet (352) and a third coolant outlet(354); a coolant recycling drum (800) having a drum outlet (812) influid communication with the third coolant inlet (352) and furtherhaving drum inlet (822) in fluid communication with the third coolantoutlet (354); and a recycling pump (810) interposed between the drumoutlet (812) and the third coolant inlet (352), the recycling pump (810)configured to supply coolant (815) under pressure to the third coolantinlets (352).
 21. The pulse combustion heat exchanger (1000) accordingto claim 20, further comprising: a third restriction orifice (RO3)positioned between the coolant recycling drum (800) and the thirdcoolant inlet (352).
 22. The pulse combustion heat exchanger (1000)according to claim 8, further comprising: a plurality of fuel injectors(370A, 370B) location in the fuel inlet section (200), each fuelinjector including a fuel injector conduit (372A, 372B) connected to afuel injector distributor (374A, 374B), wherein: the fuel injectorconduit (372A, 372B) is configured to accept said fuel (1A2), and fuelinjector distributor (374A, 374B) is configured to transfer the fuel(1A2) from the fuel injector conduit (372A, 372B) into the mixingsection (300).